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2019-19-16: The FAA is superseding Airworthiness Directive (AD) 2019-05- 09, which applied to certain Airbus SAS Model A320-251N and -271N airplanes, and Model A321-253N airplanes. AD 2019-05-09 required repetitive detailed inspections of certain electrical harnesses for discrepancies, and corrective actions if necessary. AD 2019-05-09 also provided an optional terminating modification for the repetitive detailed inspections. This AD retains the actions of AD 2019-05-09, and adds a requirement for a terminating modification for the repetitive detailed inspections, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of low clearance between the electrical harness and nearby hydraulic pipes in the inboard trailing edge of the wing. The FAA is issuing this AD to address the unsafe condition on these products.
86-26-04: 86-26-04 CESSNA: Amendment 39-5503. Applies to the following airplanes certificated in any category: MODELS SERIAL NUMBERS 120, 140 All 140A All 150 17001 thru 17,999; 59001 thru 59018 150A, 150B, 150C, 150D 150E, 150F, 150G, 150H 150J, 150K, 150L 15059019 thru 15072003 F150F, F150G, F150H F150-0001 thru F150-0529 F150K F15000530 thru F15000658 170, 170A, 170B All 172, 172A 28,000 thru 29,999 36,000 thru 36,999 46,001 thru 47,746 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K 17247747 thru 17259223 F172D, Fl72E, F172F, F172G F172-0001 thru Fl72-0654 F172H F17200655 thru F17200754 FR172E, FR172F, FR172G FR1720000l thru FR17200225 P172D All 175, 175A, 175B, 175C All 177, 177A, 177B 17700001 thru 17701530 180, 180A 30000 thru 32999 180A, 180B, 180C, 50,000 thru 50911 180D, 180E, 180F, 180G, 180H 18050912 thru 18052175 182, 182A, 182B, 33,000 thru 34999 182C 51,001 thru 53,007 182D, 182E, 182F 182G, 182H, 182J 182K, 182L, 182M, 182N 18253008 thru 18260445 185, 185A, 185B, 185C 185D, 185E, A185E 185-0001 thru 185-1599 A185E 18501600 thru 18501832 190, 195, 195A, 195B All 205, 205A All 206 All U206, U206A, U206B, U206C, U206D, TU206A, TU206B, TU206C, TU206D 206-0276 thru 206-1444 U206E, TU206E 20601445 thru 20601587 P206, P206A, P206B, P206C, P206D, TP206A, TP206B, TP206C, TP206D P206-0001 thru P206-0603 P206E, TP206E P20600604 thru P20600647 207, T207 2070001 thru 20700190 210 57001 thru 57575 210A, 210B, 210C, 210D 210E, 210F, 210G, 210H, 210J, 210K, T210K 21057576 thru 21059351 T210G, T210H, T210J All 336 All 337, 337A, 337B, 337C 337D, 337E, T337B, T337C, T337, T337E 33700001 thru 33701316 Compliance: Required within the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To prevent slippage of the pilot/co-pilot shoulder harnesses, accomplish the following on airplanes which have had the shoulder harnesses installed by any of the following Cessna Accessory Kits (AK): AK140-10 AK182-75 AK210-172 AK150-7 AK195-10 AK210-173 AK150-121 AK210-77 AK210-174 AK170-10 AK210-93 AK336-32 AK177-10 AK210-171 AK336-36 AK336-103 (a) Inspect the upper shoulder harness adjuster in accordance with Cessna Single Engine Service Bulletin, SEB86-8 or Cessna Multi-Engine Service Bulletin, MEB86-22, as appropriate, for the presence of a retainer spring. If installed, prior to further flight, remove the spring and stamp out the -401 identification number in accordance with the service bulletin instructions. NOTE: There are two adjusters in each shoulder harness assembly. This AD applies only to the upper adjuster. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) The holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him may conduct the inspections and modifications required by this AD on any airplane not used in air carrier service. The person accomplishing this AD must make the appropriate maintenance record entry as prescribed by FAR 91.173. (d) Any equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Cessna Aircraft Company, Customer Service, P.O. Box 1521, Wichita, Kansas 67201; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective January 6, 1987.
83-07-11: 83-07-11 WYTWORNIA SPRZETU KOMUNIKACYJNEGO, PZL MIELEC: Amendment 39-4614. Applies to Model PZL M18 (all Serial Numbers up through and including 1Z009-30) airplanes certificated in any category. Compliance: Required within the next 100 landings, unless already accomplished. To prevent brake failure which could result in an accident during landing or rollout, accomplish the following: a) Remove the left and right braking levers Part Number (P/N) D52.310.00.1 or D52.310.00.2 from the airplane and modify them in accordance with Wytwornia Sprzetu Komunikacyjnego Bulletin U/044/82, Sections III(1) through (5). b) Install the modified levers on the airplane with the new bolt P/N D52.300.03.2 and check for proper operation in accordance with Bulletin U/044/82, Sections III(6) and (7). c) Record compliance with this Airworthiness Directive (AD) in the aircraft maintenance log book. d) Operators who do not keep records of landings must substitute airplane hours time-in-service at the rate of 2 landings per hour time-in-service. e) Airplanes may be flown in accordance with FAR 21.197 to a location where this Airworthiness Directive (AD) can be accomplished. f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 14, 1983.
98-11-11: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235 series airplanes, that requires modification of the passenger and crew doors and repetitive visual inspections, adjustments, and tests of the passenger and crew door latching and locking systems to ensure correct operation. 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 inadvertent opening of a door during flight of the airplane, which could result in rapid decompression of the passenger cabin.
71-13-01: 71-13-01 AVCO LYCOMING: Amdt. 39-1231. Applies to TIO 540-A series engines with serial numbers lower than 1931-61. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible failures of the fuel injector manifold to nozzle tube assemblies accomplish the following: 1. Visually inspect each tube assembly for fuel stains, cracks, dents and bend radii under 5/8 inch. Replace cracked or dented lines and increase bends to 5/8 inch or more without denting or kinking before further flight. 2. Install support clamps in accordance with the instructions contained in Lycoming Service Bulletin No. 335 or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective June 22, 1971.
97-17-01: 97-17-01 BOEING: Amendment 39-10102. Docket 96-NM-152-AD. \n\n\tApplicability: Model 737-100 and -200 series airplanes equipped with Bendix main wheel assemblies having part number 2601571-1, certificated in any category. \n\n\tNOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes 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 (c) 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. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent failure of the wheel flanges, which could result in damage to the hydraulics systems, jammed flight controls, loss of electrical power, or other combinations of failures and consequent reduced controllability of the airplane, accomplish the following: \n\n\tNOTE 2: Allied Signal, Aircraft Landing Systems, Service Information Letter #619, dated February 26, 1997, is an additional source of service information for appropriate wheel half serial numbers.\n \n\t(a)\tFor airplanes equipped with a Bendix main wheel assembly having part number (P/N) 2601571-1 with an inboard wheel half with serial number (S/N) B-5898 or lower, or S/N H-1721 or lower; or with an outboard wheel half with S/N B-5898 or lower, or S/N H-0863 or lower; accomplish the following: \n\n\t\t(1)\tWithin 180 days after the effective date of this AD, and thereafter at each tire change until the replacement required by paragraph (b) of this AD is accomplished: Accomplish the actions specified in paragraphs (a)(1)(i), (a)(1)(ii), and (a)(1)(iii) of this AD, in accordance with the Accomplishment Instructions of Allied Signal Service Bulletin No. 737-32-026, dated April 26, 1988. \n\n\t\t\t(i)\tClean any inboard and outboard wheel half specified in paragraph (a) of this AD. And\n \n\t\t\t(ii)\tInspect the wheel halves for corrosion or missing paint. If any corrosion is found, or if any paint is missing in large areas, prior to further flight, strip or remove paint, and remove any corrosion. And \n\n\t\t\t(iii)\tPerform an eddy current inspection to detect cracks of the bead seat area. \n\n\t\t(2)\tIf any cracking is found during the inspections required by this paragraph, prior to further flight, repair or replace the wheel halves with serviceable wheel halves in accordance with procedures specified in the Component Maintenance Manual. \n\n\t(b)\tFor airplanes equipped with a Bendix main wheel assembly having P/N 2601571-1 with an inboard wheel half with S/N B-5898 or lower, or S/N H-1721 or lower; or with an outboard wheel half with S/N B-5898 or lower, or S/N H-0863 or lower; accomplish the following: Within 2 years after the effective date of this AD, accomplish the actions specified in paragraphs (b)(1) and (b)(2) of this AD, in accordance with Bendix Service Information Letter (SIL) 392, Revision 1, dated November 15, 1979. Accomplishment of the replacement constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD. \n\n\t\t(1)\tRemove any inboard wheel half specified in paragraph (b) of this AD, and replace it with an inboard wheel half having P/N 2607046, S/N 5899 or greater, or S/N H-1722 or greater. And \n\n\t\t(2)\tRemove any outboard wheel half specified in paragraph (b) of this AD, and replace it with an outboard wheel half having P/N 2607047, S/N B-5899 or greater, or S/N H- 0864 or greater.\n \n\t(c)\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO. \n\n\tNOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(d)\tSpecial flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(e)\tCertain actions shall be done in accordance with Bendix Service Information Letter (SIL) 392, Revision 1, dated November 15, 1979. Certain other actions shall be done in accordance with Allied Signal Service Bulletin No. 737-32-026, dated April 26, 1988. This incorporationby 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 Allied Signal Aerospace Company, Aircraft Landing Systems, 3520 Westmoor Street, South Bend, Indiana 46628-1373. 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., suite 700, Washington, DC. \n\n\t(f)\tThis amendment becomes effective on September 16, 1997.
91-09-07: 91-09-07 BOEING: Amendment 39-6982. Docket No. 90-NM-218-AD. Supersedes AD 83- 03-01 R1. \n\n\tApplicability: Model 727 series airplanes, listed in Boeing Service Bulletin 727-53- 0153, Revision 5, dated December 14, 1989, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo ensure the structural integrity of the forward entry doorway forward frame, accomplish the following: \n\n\tA.\tVisually inspect the forward entry doorway frame for cracks in accordance with Boeing Service Bulletin 727-53-0153, dated February 1, 1980, or Revisions 1 through 5, at the earlier of the times indicated in subparagraphs A.1. or A.2. of this AD, and repeat the inspection at intervals not to exceed 3,700 landings: \n\n\t\t1.\tWithin the next 1,850 landings after March 11, 1983 (the effective date of Amendment 39-4561), or prior to accumulating a total of 25,000 landings, whichever occurs later; or \n\n\t\t2.\tWithin the next 1,850 landings after May 16, 1986, (the effective date of Amendment 39-5283), or prior to accumulating a total of 15,000 landings, whichever occurs later. \n\n\tB.\tFor airplanes modified in accordance with Boeing Service Bulletin 727-53-0153, dated February 1, 1980, through Revision 4, dated November 8, 1985, conduct the inspections described in paragraph A. of this AD prior to the accumulation of 10,000 landings after the modification or within the next 3,700 landings after the effective date of this AD, whichever occurs later. Repeat the inspection at intervals not to exceed 3,700 landings. \n\n\tC.\tCracked structure must be repaired prior to further flight, in accordance with Boeing Service Bulletin 727-53-0153, Revision 5, dated December 14, 1989, or earlier FAA- approved revisions. Repair in accordance with Revision 2 through 5 of the service bulletin constitutes terminating action for the requirements of this AD. \n\n\tD.\tModification in accordance with Boeing Service Bulletin 727-53-0153, Revision 5, dated December 14, 1989, constitutes terminating action for the requirements of this AD. \n\n\tE.\tFor the purpose of complying with this AD, subject to acceptance by the assigned FAA Principal Maintenance Inspector, the number of landings may be determined by dividing each airplane's number of hours time-in-service by the operator's fleet average time from takeoff to landing for the airplane type. \n\n\tF.\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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may concur or comment and then send it to the Manager, Seattle ACO.\n \n\tG.\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 documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tAirworthiness Directive 91-09-07 supersedes AD 83-03-01 R1 (Amendment 39-5283), which revised AD 83-03-01 (Amendment 39-4561). \n\n\tThis amendment (39-6982, AD 91-09-07) becomes effective on May 28, 1991.
2019-19-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of disconnections of certain hinge arms of the bulk cargo door (BCD) due to disbonding of the hinge arm bushes. This AD requires either modifying and re-identifying affected BCDs or replacing affected BCDs, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
87-01-03: 87-01-03 AEROSPATIALE: Amendment 39-5492. Applies to Model ATR-42 airplanes listed in Aerospatiale Service Bulletin ATR 42-79-0002 dated September 3, 1986, certificated in any category. To ensure acceptable engine anti-icing capability, accomplish the following within 10 days after the effective date of the AD, unless previously accomplished. A. Modify the engine oil cooler thermostatic valve system, in accordance with Aerospatiale Service Bulletin ATR 42-79-0002, dated September 3, 1986. B. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. All persons affected by this directive who have not already received theappropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This document 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. This amendment becomes effective January 20, 1987.
97-15-06: 97-15-06 BOEING: Amendment 39-10079. Docket 97-NM-123-AD.\n \n\tApplicability: Model 737, 747, 757, and 767 series airplanes equipped with IPECO pilots' seats; as listed in Boeing Service Bulletins 737-25-1334, 747-25-3132, 757-25-0183, and 767-25-0244; all dated December 19, 1996; certificated in any category. \n\n\tNOTE 1: This AD applies to each airplane 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 airplanes 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 (b) 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 requestshould include specific proposed actions to address it. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent uncommanded movement of the pilots' seats during acceleration and take-off of the airplane; accomplish the following: \n\n\t(a)\tWithin 90 days after the effective date of this AD, perform a one-time operational test of the pilots' seats and the seat locks to determine that the lock pin of the seat track fully engages in all lock positions of the seat track, in accordance with Boeing Service Bulletin 737-25-1334 (for Model 737 series airplanes), 747-25-3132 (for Model 747 series airplanes), 757-25-0183 (for Model 757 series airplanes), or 767-25-0244 (for Model 767 series airplanes); all dated December 19, 1996; as applicable. \n\n\t\t(1)\tIf the seat lock pin fully engages in all lock positions of the seat track, no further action is required by this AD. \n\n\t\t(2)\tIf the seat lock pin does not fully engage in all positions of the seat track, priorto further flight, re-align the seat tracks, in accordance with the applicable service bulletin specified in paragraph (a) of this AD. \n\n\t(b)\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO. \n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.\n \n\t(c)\tSpecial flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(d)\tThe actions shall be done in accordance with Boeing Service Bulletin 737-25-1334, dated December 19, 1996; Boeing Service Bulletin 747-25-3132, dated December 19, 1996; Boeing Service Bulletin 757-25-0183, dated December 19, 1996; or Boeing Service Bulletin 767-25-0244, dated December 19, 1996. 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 98124-2207. 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., suite 700, Washington, DC. \n\n\t(e)\tThis amendment becomes effective on July 31, 1997.