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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.
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.
78-01-16: 78-01-16 MCDONNELL DOUGLAS: Amendment 39-3117. Applies to Model DC-9 and Military C-9 Series Airplanes certificated in all categories, Fuselage Numbers 1 through 851, inclusive which correspond to the factory serial numbers listed in Douglas DC-9 Service Bulletin No. 54-31, dated August 24, 1976, or later FAA approved revisions. \n\n\tTo detect cracks and prevent possible failure of the engine pylon aft upper spar straps (caps) comply with the following: \n\n\t(a)\tFor airplanes with 35,000 or more landings on the effective date of this AD, within the next 600 landings unless already accomplished within the last 1800 landings and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(b)\tFor airplanes with 30,000 to 34,999 landings on the effective date of this AD, within the next 900 landings, unless already accomplished within the last 1500 landings, and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(c)\tFor airplanes with 25,000 to 29,999 landings on the effective date of this AD, within the next 1200 landings, unless already accomplished within the last 1200 landings, and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(d)\tFor airplanes with 15,000 to 24,999 landings on the effective date of this AD, within the next 2,000 landings, unless already accomplished within the last 400 landings, and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(e)\tFor airplanes with less than 15,000 landings on the effective date of this AD, within the first 2,000 landings, after accumulating 15,000 landings, and thereafter at intervals not to exceed 2400 landings, accomplish Paragraph (f). \n\n\t(f)\tAs required by Paragraphs (a) through (e): \n\n\t\t(1)\tUltrasonically inspect the engine pylon aft upper spar straps (caps), Part Number 9958154-5/-6 or 9958154-37/-38 per Paragraph 2.B of Douglas DC-9 Service Bulletin A54-31 dated December 22, 1976 orlater FAA approved revision, or an alternate method approved by the Chief, Aircraft Engineering Division, Western Region. If there is evidence of cracking, magnetic particle inspection per Paragraph 2.C may be used to confirm the evidence of cracking. \n\n\t\t(2)\tIf cracks are detected, before further flight replace the strap with new Part Numbers 9958154-5/-6 or 9958154-37/-38 and resume the inspections after the part has accumulated 15,000 landings or modify in accordance with Douglas Service Bulletin 54-31 dated August 24, 1976 or later FAA approved revision. \n\n\t\t(3)\tAt the option of the operator, the ultrasonic inspection may be deleted if the magnetic particle inspection is accomplished. If the magnetic particle inspection procedure is used, after two bearing replacements it is necessary to replace the strap with a new Part Number 9958154-5/-6 or 9958154-37/-38 or modified per Douglas Service Bulletin 54-31 dated August 24, 1976 or later FAA approved revision. \n\n\t(g)\tUpon completion of modification of the engine pylon rear spar straps (caps) per Douglas Service Bulletin 54-31 dated August 24, 1976 or later FAA approved revision the inspection requirements of this AD are terminated. \n\n\t(h)\tFor the purpose of complying with this AD, if records of landings are not available, the number of landings for the purpose of establishing initial compliance may be determined by dividing each airplane's hours in service by the operator's appropriate fleet average time from takeoff to landing. This procedure is subject to acceptance by the assigned FAA maintenance inspector. \n\n\t(i)\tSpecial flight permits may be issued in accordance with FAR's 21.197 and 21.199 to authorize operation of an airplane to a base for the accomplishment of the inspections required by this AD. \n\n\tThis Amendment becomes effective February 13, 1978.
2019-19-12: The FAA is superseding Airworthiness Directive (AD) 2018-10-07 for Sikorsky Aircraft Corporation (Sikorsky) Model S-76C helicopters. AD 2018-10-07 required inspecting the engine collective position transducer (CPT). This new AD retains the requirements of AD 2018-10-07 and expands the applicability. This AD is prompted by the determination that an additional part-numbered engine CPT is affected by the same unsafe condition. [[Page 53009]] The FAA is issuing this AD to address the unsafe condition on these products.
83-24-02: 83-24-02 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39-4771. Applies to all Model Falcon 10 airplanes specified in the Planning Information of the service bulletins, certificated in all categories. To assure adequate exterior emergency lighting accomplish the following unless previously accomplished: A. Within the next 400 hours time in service or 270 days, whichever occurs first, after the effective date of this AD, perform the actions described in the Accomplishment Instructions of one of the following Service Bulletins: (1) Avions Marcel Dassault-Breguet Aviation AMD-BA F10 0222, (F10 33 003), dated November 12, 1981, for airplanes completed by AMD-BA with option 25-20-02, or (2) Falcon Jet Corporation No. 15 (ATA No. 33-1), dated August 17, 1983, for airplanes completed in the United States. B. 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. NOTE: Incorporation of the emergency exit lighting features of Supplemental Type Certificate SA4996SW constitutes compliance with this AD. 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 inspections and/or modifications required by this AD. This amendment becomes effective December 23, 1983.
97-15-16: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-15-16, which was sent previously to all known U.S. owners and operators of BHTC Model 430 helicopters by individual letters. This AD requires inspections of all 4 main rotor adapter assemblies for evidence of flapping contact between the adapter liners and the upper stop assembly plugs, and for evidence of lead-lag contact between the adapter pads and the yoke assembly; installing a never-exceed-velocity (VNE) placard; marking the airspeed indicator to reflect the airspeed restriction; installing a slippage mark on the airspeed indicator glass and instrument case; and inserting revisions to the rotorcraft flight manual to reflect the airspeed revision. This amendment is prompted by a report of a main rotor tip path plane separation, which occurred during a ferry flight at an airspeed of more than 140 knots indicated airspeed (KIAS). The actions specified by this AD are intended to prevent tip path plane separation, increased vibrations, possible damage to the main rotor system, and subsequent loss of control of the helicopter.
62-22-02: 62-22-02 PRATT & WHITNEY: Amdt. 496 Part 507 Federal Register October 16, 1962. Applies to All Pratt & Whitney Aircraft JT3D-1 Turbofan Engines. Compliance required as indicated. To preclude failure of the fourth stage compressor rotor disc, P/N 393504, accomplish the following: (a) For engines previously inspected by the procedure described in paragraph (c) or for engines which have been overhauled, inspect in accordance with paragraph (c) as follows: (1) Inspect engines which have accumulated 235 or more hours' time in service since the last such inspection or engine overhaul within the next 130 hours' time in service after the effective date of this AD, and every 365 hours' time in service thereafter. (2) Inspect engines which have accumulated less than 235 hours' time in service since the last such inspection or engine overhaul, prior to the accumulation of 365 hours' time in service since the last such inspection or engine overhaul and every 365 hours' time in service thereafter. (b) For engines which have not previously been inspected by the procedure described by paragraph (c) and which have not been overhauled, inspect in accordance with paragraph (c) as follows: (1) Inspect engines with 300 or more hours' time in service within the next 65 hours' time in service after the effective date of this AD, and every 365 hours' time in service thereafter. (2) Inspect engines with less than 300 hours' time in service prior to the accumulation of 365 hours' time in service and every 365 hours' time in service thereafter. (c) Remove the front accessory drive support assembly (NI gearcase) and the front accessory drive main spur gear (NI gearcase coupling). Using a strong light, visually inspect the fourth stage compressor rotor disc in the area between the disc bore and the spacer shoulder on the disc. If cracking is found, remove the engine for disc replacement prior to further flight. (d) When fourth stagecompressor disc P/N 468304 is installed in place of P/N 393504, the repetitive inspections required by this AD are no longer required. (e) The requirement for main oil screen inspections per AD 61-24-01 does not apply when the No. 1 bearing compartment is exposed for this disc inspection. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Pratt & Whitney Aircraft telegraphic message of August 21, 1962, to all JT3D operators, covers the same subject.) This directive effective October 16, 1962.
2019-20-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD requires repetitive inspections for cracking of the left and right hand side outboard chords of frame fittings and failsafe straps at a certain station, and repair if any cracking is found. This AD was prompted by reports of cracking discovered in this area. The FAA is issuing this AD to address the unsafe condition on these products.
98-09-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections of the fuselage skin to detect corrosion or fatigue cracking around and under the chafing plates of the wing root; and corrective actions, 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 detect and correct fatigue cracks and corrosion around and under chafing plates of the wing root, which could result in reduced structural integrity of the airplane.
80-12-04: 80-12-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-3790. Applies to Model SA-330 series helicopters, certificated in all categories, with tail rotor blades P/N 330.12.0000 all dash numbers, P/N 330.12.0005 all dash numbers, or P/N 330.12.0006 all dash numbers installed. To prevent failure of the tail rotor blades, accomplish the following: (a) Within the next five hours time in service after the effective date of this AD or before further flight following the last flight of the day after the effective date of this AD, whichever occurs sooner, and thereafter at intervals not to exceed five hours time in service from the last inspection, and before further flight following the last flight of each day, inspect the tail rotor blade skin in the root area of all tail rotor blades for cracks by visual means in accordance with Aerospatiale Service Bulletin No. 05.59, dated March 23, 1979, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (b) If, during any inspection required by this AD, any cracks are found, before further flight, remove the cracked blade from service and replace with a serviceable part of the same part number, or a serviceable interchangeable tail rotor blade as defined by Section 5.11 of the Aerospatiale Model SA-330 series helicopters Maintenance Manual, Chapter 65.21 or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, and continue to inspect in accordance with paragraph (a) of this AD. This amendment becomes effective June 2, 1980, as to all persons except those persons to whom it was made immediately effective by the telegram issued April 6, 1979, which contained this amendment.
79-24-02: 79-24-02 MITSUBISHI AIRCRAFT INTERNATIONAL, INC., (MAI): Amendment 39-3612. Applies to MAI Model MU-2B series, serial numbers 354SA, 356SA, 374SA, 387SA, 392SA, 393SA, 709SA, 723SA, 728SA, and other aircraft which have previously complied with Service Recommendation No. SR017/28-001, dated July 25, 1979; MU-2B-40, serial numbers 395SA through 412SA, 414SA, and 416SA; Model MU-2B-60, serial numbers 731SA through 747SA and 749SA through 757SA. Compliance is required within the next 50 hours' time in service after the effective date of this airworthiness directive, unless already accomplished, except that the airplane may be flown in accordance with FAR 21.197 to a base where the modifications can be performed. To prevent pumping fuel overboard, accomplish the following: Modify outer fuel tank switch wiring in accordance with Mitsubishi Aircraft International Service Bulletin No. SB013/28-001, dated October 18, 1979; or Service Bulletin No. SB014/28-002, dated October 18, 1979, as applicable; or an equivalent method. Mitsubishi Aircraft International Inc., Service Bulletin No. SB013/28-001 and Service Bulletin No. SB014/28-002 pertain to and provide instructions for accomplishing the intent of this AD. The manufacturer's procedures identified and described in this directive are incorporated herein and made a part thereof pursuant of U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Mitsubishi Aircraft International, Inc., Post Office Box 3848, San Angelo, Texas 76901. These documents may also be examined at Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective November 21, 1979.