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74-06-01: 74-06-01 PIPER: Amendment 39-1799 is amended by Amendment 39-1977. Applies to Piper Models PA-23-235, PA-23-250 and PA-E23-250 airplanes certificated in all categories with AiResearch turbosuperchargers installed in accordance with STC SA852WE, SA909WE or SA978WE,. or installed in accordance with Piper Aircraft Corporation Drawing 32016. Compliance required as indicated, unless previously accomplished. To minimize fire hazards related to engine compartment fires, accomplish the following in accordance with AiResearch Aviation Company Service Bulletin No. 14.1.10, dated February 6, 1974 or later FAA-approved revision, for serial numbers 27-2505 and subsequent (Aztec C, Aztec D, Aztec E), and, in accordance with AiResearch Service Bulletin No. 14.1.11, dated February 6, 1974 or later FAA-approved revision for serial numbers 27-1 through 27-2504 (Aztec, Aztec B, Apache 235): (a) Within the next 25 hours' time in service after the effective date of this airworthinessdirective, add drainage provisions in the airscoops, AiResearch Part No. 286-P23-066-5, of airplanes serial numbers 27-2505 and subsequent. (b) Within the next 600 hours' time in service or 365 days after March 18, 1974, whichever occurs first: (1) For airplanes serial numbers 27-1 through 27-2504: (i) Replace the existing turbosupercharger oil tanks with AiResearch Part No. 286-P23-028-81F oil tanks. (ii) Install AiResearch Part No. 286-P23-028-231 fire shrouds and seal all openings in the fire shrouds. (iii) Add drainage provisions in the oil tank fairings, AiResearch Part No. 286-P23-057. (2) For airplanes serial number 27-2505 and subsequent: (i) Replace the existing turbosupercharger oil tanks with AiResearch Part No. 286-P23-028-111F oil tanks. (ii) Seal all openings in the fire shrouds, AiResearch Part No. 286- P23-064-153. (c) Equivalent modification may be approved by the Chief, Aircraft Engineering Division, FAA WesternRegion. (d) Aircraft may be flown to a base where the maintenance required by this airworthiness directive may be performed per FARs 21.197 and 21.199. NOTE: For the requirements regarding the listing of compliance of and method of compliance with this airworthiness directive in the permanent maintenance record of the airplane, see FAR 91.173. NOTE: The extended compliance time authorized by this amendment to AD 74-06-01, as set forth in (b) above, shall be retroactive to September 14, 1974, to permit aircraft operations beyond 180 days after March 18, 1974. Amendment 39-1799 became effective March 18, 1974. This Amendment 39-1977 becomes effective October 2, 1974.
97-24-10: This amendment adopts a new airworthiness directive (AD) that applies to Burkhart Grob Luft-und Raumfahrt, GmbH. (Grob) Model G 103 Twin Astir sailplanes. This action requires replacing the airbrake over-center lever and installing new inspection holes. The AD is the result of cracked airbrake over-center levers found during routine inspections. The actions specified by this AD are intended to prevent an asymmetrical airbrake deployment, which could result in an uncontrollable roll and possible loss of control of the sailplane.
2019-16-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of unreliable performance of the water and fuel scavenge system; failure of the fuel scavenge function can cause trapped fuel, resulting in unavailable fuel reserves. This AD requires incorporating operating limitations; or modifying the water and fuel scavenge systems in the fuel tanks, modifying the fuel jettison system, making electrical changes in the main equipment center, modifying the wiring in certain panels, and installing new software. We are issuing this AD to address the unsafe condition on these products.
2019-19-17: The FAA is superseding Airworthiness Directive (AD) 2000-03-20 R1, which applied to all Airbus SAS Model A300 B4-601, B4-603, and B4- 620, Model A300 B4-600R series, and Model A300 F4-605R airplanes. AD 2000-03-20 R1 required repetitive inspections to detect cracks on the forward fittings in the radius of a certain frame, adjacent to the tension bolts in the center section of the wings, and various follow-on actions. This AD retains the requirements of AD 2000-03-20 R1, adds new airplanes to the applicability, and introduces new compliance times for the required inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by reports of cracking due to fatigue-related stress in the radius of frame 40, adjacent to the tension bolts at the center/ outer wing junction. The FAA is issuing this AD to address the unsafe condition on these products.
96-25-06: 96-25-06 SAAB AIRCRAFT AB: Amendment 39-9848. Docket 95-NM-201-AD. Applicability: Model SAAB SF340A series airplanes, serial numbers 004 through 159 inclusive; and Model SAAB 340B series airplanes, serial numbers 160 through 379 inclusive; certificated in any category. NOTE 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 specificproposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent high bearing stress on the bushings in the flap fittings, which could result in jamming of the flaps and consequent reduced controllability of the airplane, accomplish the following: (a) Within 800 hours time-in-service after the effective date of this AD: Perform a visual inspection to detect damage or cracking of the forward and aft attachment lugs of the flap fittings at wing station (WS) 123.38, in accordance with Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. (1) If no cracking or damage is found, and the flap fittings have not been modified or replaced, repeat the visual inspection thereafter at intervals not to exceed 800 hours time-in-service. (2) If any cracking is found, prior to further flight, replace the flap fittings with new improved flap fittings, and install improved bushings, in accordance with the Accomplishment Instructions (Modification 2628 - Part 3) of the service bulletin. After this modification is accomplished, no further action is required by this paragraph. (b) Within 4,500 hours time-in-service after the effective date of this AD, perform an inspection to determine the size of the inboard and outboard holes (swaged bushings) of the flap fittings, and to detect loose swaged bushings, in accordance with Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. (1) If the sizes of the holes are within the limits specified in the service bulletin, and if no loose swaged bushings are found, prior to further flight, install improved bushings in accordance with the Accomplishment Instructions (Modification 2628 - Part 1) of the service bulletin. After this modification is accomplished, no further action is required by this AD. (2) If the size of any hole is outside the limits specified in the service bulletin, or if any loose swaged bushing is found, prior to further flight, install oversize bushings in the flap fittings, and install improved bushings, in accordance with the Accomplishment Instructions (Modification 2628 - Part 2) of the service bulletin. After this modification is accomplished, no further action is required by this AD. (c) 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, ANM-113, 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, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) Special 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. (e) The inspections, replacement, and installations shall be done in accordance with Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. 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 SAAB Aircraft AB, SAAB Aircraft Product Support, S-581.88, Link ping, Sweden. 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. (f) This amendment becomes effective on January 27, 1997.
83-26-01: 83-26-01 BRITISH AEROSPACE: Amendment 39-4785. Applies to Model HS 748 airplanes, certificated in all categories, for the series listed in the service bulletins below. To prevent the development of unsafe conditions, the following three actions are required, unless previously accomplished: A. To prevent progression of cracks in the main landing gear inboard pivot brackets, part numbers 15F11365 and 16F11365, inspect the inboard pivot brackets for corrosion, loose bolts, and cracks, and repair if necessary in accordance with the Accomplishment Instructions of British Aerospace HS 748 Service Bulletin 57/59, dated October 1979, prior to accumulating 25,000 landings or within the next 750 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not exceeding 1,500 landings from the last inspection. If inboard pivot brackets are corroded to a depth greater than 0.060 inch, the operators of the aircraft must contact the manufacturer for repair instructions. B. To detect cracks in the joints between the tailplane center torsion box and outer tailplanes, inspect and repair, if necessary, the tailplane front and rear spar joint plates and webs in accordance with the Accomplishment Instructions of British Aerospace Aircraft Group HS 748 Service Bulletin 55/19, Revision 1, dated September 1982, prior to the accumulation of 18,000 hours time in service or within the next 750 hours time in service after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 hours time in service. C. Modify the aileron control quadrant assemblies on airplanes equipped with aileron control quadrant assemblies part numbers 1R4583 and 2R4583 in accordance with paragraph 2.B of British Aerospace Aircraft Group HS 748 Service Bulletin 27/75 dated April 4, 1978, prior to the accumulation of 12,000 hours time in service or within the next 750 hours time in service after the effective date ofthis AD, whichever occurs later. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. 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 inspections and/or modifications required by this AD. This amendment becomes effective January 30, 1984.
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.