Results
2013-02-01: We are adopting a new airworthiness directive (AD) for Bell Model 206L, 206L-1, 206L-3, and 206L-4 helicopters. This AD requires inspecting certain hydraulic servo actuator assemblies (servo) for a loose nut, shaft, and clevis assembly, modifying or replacing the servo as necessary, and reidentifying the servo. This AD is prompted by an investigation after an accident and the determination that there was a loose connection due to improper lock washer installation. These actions are intended to detect loose or misaligned parts of the servo to prevent failure of the servo and subsequent loss of control of the helicopter.
98-17-04: This amendment adopts a new airworthiness directive (AD) that is applicable to Hartzell Propeller Inc. HC-E4A-3(A,I,J) series propellers. This action requires a one-time inspection of the propeller blade counterweight clamps for thread damage in the bolt holes, and, if necessary, replacement with serviceable parts. This amendment is prompted by a report of a counterweight clamp bolt hole thread failure that resulted in the separation of the counterweight and the separation of a blade following impact with the counterweight. The actions specified in this AD are intended to prevent propeller blade counterweight clamp bolt hole thread failure, which can result in counterweight and propeller blade separation, and possible damage to the aircraft.
2012-26-04: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200PF, and -200CB series airplanes powered by Rolls-Royce engines. That AD currently requires repetitive inspections of the shim installation between the drag brace fitting vertical flange and bulkhead, and repair if necessary; for certain airplanes, an inspection for cracking of the four critical fastener holes in the horizontal flange, and repair if necessary; and, for airplanes without conclusive records of previous inspections, performing the existing actions. This new AD reduces the repetitive inspection interval; adds repetitive detailed inspections for cracking of the bulkhead, and repair if necessary; allows an extension of the repetitive intervals for certain airplanes by also doing repetitive ultrasonic inspections for cracking of the bulkhead, and repair if necessary; and provides an option for a high frequency eddy current inspection for cracking of the critical fastener holes, and repair if necessary. This action also adds a terminating action for certain repetitive inspections. This AD was prompted by reports of loose fasteners and cracks at the joint common to the aft torque bulkhead and strut-to-diagonal brace fitting, and one report of such damage occurring less than 3,000 flight cycles after the last inspection. We are issuing this AD to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-to-diagonal brace fitting, which could result in damage to the strut and consequent separation of the strut and engine from the airplane.
98-17-08: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive inspections to detect any discrepancy in the sealwire of the fireguards of the engine fire shut-off system, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent inadvertent closure of the fire shut-off valves due to ineffective or absent sealwires, which could result in in-flight engine shutdown.
2008-18-02: The FAA is superseding an existing airworthiness directive (AD), which applies to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. That AD currently requires repetitive tests for free movement of the capsule/bearing of the nose landing gear (NLG), and related investigative and corrective actions. This new AD requires a modified test for free movement of the capsule/bearing of the NLG at reduced repeat intervals, and replacement of the NLG assembly with a modified assembly. This AD results from additional reports of the NLG failing to extend fully on an airplane that had been inspected in accordance with AD 2004-14-07. We are issuing this AD to prevent failure of the NLG to extend fully, which could result in reduced controllability of the airplane during landing. DATES: This AD becomes effective March 27, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 27, 2009. On August 13, 2004 (69 FR 41413, July 9, 2004), the Director of the Federal Register approved the incorporation by reference of BAE Systems (Operations) Limited Alert Service Bulletin J41-A32-082, Revision 1, dated February 20, 2004.
95-24-05 R1: 95-24-05 R1 MCCAULEY ACCESSORY DIVISION, THE CESSNA AIRCRAFT COMPANY: Amendment 39-9566. Docket 94-ANE-47. Revises AD 95-24-05, Amendment 39-9437. Applicability: McCauley Accessory Division, The Cessna Aircraft Company, Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 series propellers, incorporating the following Hub Models: D3AF32C35-( ) D3AF32C80-( ) 3AF34C92-( ) 3AF32C72-( ) 3AF34C86-( ) 3AF32C93-( ) 3AF34C74-( ) 3AF32C87-( ) 3AF32C75-( ) D3AF32C87-( ) The parentheses used in the above list indicate the presence or absence of an additional letter(s) which vary the basic propeller hub model designation. These letter(s) define minor changes that do not affect interchangeability or eligibility, and therefore, this airworthiness directive (AD) still applies regardless of whether these letters are present or absent on the propeller hub model designation. These propellers are installed on but not limited to the following aircraft: Beech 58, 58A, 95-C55, -C55A, -D55, -D55A, -E55, -E55A. British Aerospace B-206 Series 2. Cessna 310K, 310L, 310N, 310P, 310Q, 310R, T310P, T310Q, T310R, 320D, 320E, 320F, 335, 340, 340A, 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, 421A, 421B. Colemill Executive 600 (Conversion of Cessna 310I, 310J, 310K, 310L, 310N). RAM Conversion of Cessna 340. NOTE 1: The above is not an exhaustive list of aircraft which may contain the affected McCauley Model C35, C72, C74, C75, C80, C86, C87, C92, and C93 series propellers, incorporating Models D3AF32C35, 3AF32C72, 3AF34C74, 3AF32C75, D3AF32C80, 3AF34C86, 3AF32C87, D3AF32C87, 3AF34C92, and 3AF32C93 propeller hubs because of installation approvals made by Supplemental Type Certificate or Federal Aviation Administration (FAA) Form 337 "Major Repair and Alteration," etc. It is the responsibility of the owner, operator and person returning the aircraft to service to determine if an aircraft has an affected propeller. NOTE 2: This AD applies to each propeller 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 propellers that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (g) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any propeller from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent propeller blade separation due to a cracked propeller hub, which could result in separation of the engine from the aircraft and subsequent loss of aircraft control, accomplish the following: (a) Within the next 25 hours time in service (TIS) after December 18, 1995 (the effective date of AD 95-24-05), unless already accomplished within the last 35 hours TIS, and thereafter at intervals not to exceed 60 hours TIS, perform a visual inspection for cracks and, if crack indications are found or suspected, confirm cracks by a dye penetrant inspection on propeller hubs in accordance with McCauley Accessory Division, The Cessna Aircraft Company, Service Bulletin (SB) No. 200C, dated January 20, 1994. Any propeller hubs found cracked during this inspection are to be permanently retired from service and replaced with a serviceable hub modified in accordance with paragraph (c) of this AD, or with an equivalent initial production propeller which has incorporated a hub containing oil with red dye. (b) For affectedpropellers identified with the change letter "R" following the hub model designation and having an oil-fill plug in the side of the hub, compliance is required only with paragraphs (d) and (f) of this AD. (c) Perform a one-time eddy current inspection and modify serviceable propeller hubs in accordance with the following schedule and requirements: Propeller Time-In-Service (TIS) Compliance Required on the effective date of this AD. Greater than 900 hours or 59 calendar Within the next 300 hours or at the next months since last overhaul/penetrant annual inspection or by December 31, 1996, inspection or installed new, or prior TIS whichever occurs first. unknown. Less than or equal to both 900 hours Prior to the accumulation of 1,200 hours and 59 calendar months since last or 60 calendar months since last overhaul/penetrant inspection or overhaul/penetrant inspection or installed installed new. new, whichever occurs first. (1) Perform a one-time eddy currentinspection for cracks in the threaded areas of the propeller hubs in accordance with McCauley Accessory Division, The Cessna Aircraft Company, Service Letter (SL) No. 1993-11A, dated June 20, 1995. (2) Any propeller hubs found cracked during the eddy current inspection are to be permanently retired from service and replaced with a serviceable hub modified in accordance with paragraph (c) of this AD, or with an equivalent initial production propeller which has incorporated a hub containing oil with red dye. (3) Modify affected propeller hubs to contain oil with red dye, in accordance with McCauley Accessory Division, The Cessna Aircraft Company, SL No. 1993-11A, dated June 20, 1995. Completion of this modification of the hub to contain oil with red dye constitutes terminating action to the repetitive inspections required by paragraph (a) of this AD. NOTE: The modification of the propeller hub assembly to contain oil with a red dye provides an "on-condition" (in-service)means of early crack detection of the propeller assembly and also improves lubrication and corrosion protection. The oil will add approximately 4.0 lbs. to the weight of the propeller assembly. (4) Previous compliance with McCauley Accessory Division SL 1993-11, dated September 15, 1993, also constitutes compliance with paragraphs (a) and (c) of this AD. (5) Install Decal-Warning "Oil Filled", part number B-6493, in accordance with McCauley Accessory Division, The Cessna Aircraft Company, SL No. 1993-11A, dated June 20, 1995, Figure F-9. (d) If leakage of oil containing red dye is detected in service (whether during flight or while on the ground), determine, prior to further flight, the source of leakage in accordance with the procedures specified in Section A-7 of McCauley SL No. 1993-11A, dated June 20, 1995. Remove from service, prior to further flight, propeller assemblies that exhibit cracks and replace with a serviceable unit, modified in accordance with paragraph(c) of this AD, or with an equivalent initial production propeller that has incorporated a hub containing oil with red dye. Oil-filled propellers are identified with the change letter "R" following the Hub Model Designation and have an oil-fill plug in the side of the hub. (e) The "calendar month" compliance times stated in this AD allow the performance of the required action up to the last day of the month in which compliance is required. For example, a required eddy current inspection and modification 60 calendar months from last overhaul/penetrant inspection that was performed on December 15, 1991, would allow the eddy current inspection and modification to be performed no later than December 31, 1996. (f) Report in writing any cracks found during the accomplishment of paragraphs (a), (c) or (d) of this AD to the Manager, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Avenue, Room 232, Des Plaines, IL 60018; telephone (847) 294-7134, fax (847) 294-7834, within 10 days of the inspection. Information collection requirements contained in the regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (P.L. 96-511) and has been assigned OMB Control Number 2120-0056. (g) 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, Chicago Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Chicago Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Chicago Aircraft Certification Office. (h) 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 aircraft to a location where the requirements of this AD can be accomplished. (i) The inspections and modification required by this AD shall be done in accordance with the following McCauley Accessory Division, The Cessna Aircraft Company, service documents: Document No. Pages Date SB 200C 1-4 January 20, 1994 Total pages: 4. SL 1993-11A Cover Page 1 June 20, 1995 Section A 1-4 June 20, 1995 Section B 1 June 20, 1995 Section C 1 June 20, 1995 Section D 1-7 June 20, 1995 Section E 1-10 June 20, 1995 Section F 1-15 June 20, 1995 Section G 1 June 20, 1995 Section H 1-4 June 20, 1995 Section I 1-4 June 20, 1995 Total pages: 48. This incorporation by reference was approved by the Director of the Federal Register as of December 18, 1995, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from McCauley Accessory Division, The Cessna Aircraft Company, 3535 McCauley Dr., Vandalia, OH 45377-0430; telephone (513) 890-5246, fax (513) 890-6001. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (j) This amendment becomes effective on April 12, 1996.
70-25-06: 70-25-06 ROLLS-ROYCE DART: Amdt. 39-1119. Applies to Rolls-Royce Dart Models 542-4, 542-4K, 542-10, 542-10J, and 542-10K engines. Compliance is required as indicated, unless already accomplished. To prevent cracking and subsequent failure of the engine propeller shaft and damage to the coarse pitch oil line due to material inclusions in that part of the shaft between the annulus gear support diaphragms, accomplish the following: (a) For all airplanes with Rolls-Royce Dart Models 542-4, 542-4K, 542-10, 542-10J, and 542-10K engines installed except those having engine propeller shafts installed which have been supplied by Rolls-Royce with "CU" marked on the front end of the shaft, or in which each engine propeller shaft has been overhauled (including ultrasonic inspection for cracks and material inclusions) in accordance with Rolls-Royce Dart Overhaul Manual O-DA.10-AC and identified with "CU" marked on the front end of the shaft, and which are not listed in paragraph(g) of this AD, within the Next 50 hours' time in service after the effective date of this AD, install the following placard in clear view of the pilot and as close to the R.P.M. indicators as practicable: "In the event of abnormal, short duration R.P.M. increase (500-600 R.P.M.) accompanied by a drop in TGT and torque pressure at a fixed power setting, immediately feather affected propeller per AFM feathering instructions." (b) For engines which have been feathered in accordance with the placard in paragraph (a), overhaul the engine propeller shaft (including ultrasonic inspection) in accordance with Rolls-Royce Dart Overhaul Manual O- DA.10AC to determine whether material inclusions or cracks exist in that part of the engine propeller shaft between the annulus gear support diaphragms, and whether the propeller coarse pitch oil line has been damaged. If material inclusions or cracks in the propeller shaft or damage to the propeller coarse pitch oil line are found, before furtherflight replace the cracked propeller shaft and damaged propeller coarse pitch oil line with an approved serviceable part of the same part number. (c) For all engines having propeller shafts with 1200 or more hours' time in service on the effective date of this AD, within the next 450 hours' time in service and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, inspect each engine propeller shaft (including ultrasonic inspection) in accordance with Rolls-Royce Dart Aero Engine Alert Service Bulletin Number Da 72-367, dated September 17, 1969, or later ARB-approved issue or an FAA-approved equivalent. If material inclusions or cracks are detected during any inspection, before further flight replace the engine propeller shaft with an approved serviceable part of the same part number. (d) For all engines having propeller shafts with less than 1200 hours' time in service on the effective date of this AD, within a total of 1650 hours' time in service, and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, inspect each engine propeller shaft (including ultrasonic inspection) in accordance with Rolls-Royce Dart Aero Engine Alert Service Bulletin Number Da 72-367, dated September 17, 1969, or later ARB-approved issue or an FAA-approved equivalent. If material inclusions or cracks are detected during any inspection, before further flight replace the engine propeller shaft with an approved serviceable part of the same part number. (e) For Rolls-Royce Dart Models 542-4 and 542-4K engines installed in Convair airplanes, the repetitive inspections required by paragraphs (c) and (d) may be discontinued when propeller shafts are installed which have been supplied by Rolls-Royce with "CU" marked on the front end of the shaft, or which have been overhauled (including ultrasonic inspection for cracks and material inclusions) in accordance with Rolls-Royce Dart Overhaul Manual O-DA.10-AC and identified with "CU" marked on the front end of the shaft. (f) For all engines with propeller shafts installed bearing the serial numbers listed in paragraph (g), the placard required by paragraph (a) may not be removed until an FAA-approved inspection method has been developed to insure that the shafts are free from defects. (g) For Rolls-Royce Dart Models 542-4 and 542-4K engine with propeller shafts installed bearing the serial numbers listed below and which are not installed in Convair airplanes and for all Rolls-Royce Models 542- 10, 542-10J and 542-10K engines with propeller shafts installed bearing the serial numbers listed below, the repetitive inspection required by paragraphs (c) and (d) may not be discontinued until an FAA-approved inspection method has been developed to insure that the shafts are free from defects: INSPECTION OF DART PROPELLER SHAFTS IN INSTALLED ENGINES - SHAFTS FROM TOP THREE INGOT POSITION Shaft Serial No. Shaft Serial No. Shaft Serial No. Shaft Serial No. Shaft Serial No. Shaft Serial No. Shaft Serial No. HA.275 HD. 86 HE.111 HJ.135 HM.267 HR.536 HS. 8 HA.277 HD. 88 HE.115 HJ.138 HM.272 HR.547 HS. 11 HA.281 HD. 94 HE.121 HJ.143 HM.288 HR.551 HS. 13 HD. 95 HE.129 HJ.151 HM.289 HR.552 HS. 14 HB. 25 HD. 97 HE.135 HJ.153 HM.294 HR.553 HS. 16 HB. 29 HD.103 HE.139 HJ.157 HM.436 HR.580 HS. 24 HB. 30 HD.105 HE.141 HJ.165 HR.581 HS. 25 HD.107 HE.142 HJ.167 HR.315 HR.583 HS. 28 HC.846 HD.110 HE.143 HJ.168 HR.319 HR.592 HS. 29 HC.847 HD.117 HJ.173 HR.326 HR.595 HS. 30 HC.849 HD.119 HG.562 HJ.176 HR.337 HR.596 HS.129 HC.854 HD.373 HG.563 HJ.178 HR.345 HR.597 HS.131 HC.856 HD.376 HG.570 HJ.180 HR.346 HR.600 HS.139 HC.857 HD.377 HG.571 HJ.189 HR.439 HR.601 HS.140 HC.858 HD.391 HG.572 HJ.190 HR.442 HR.780 HS.142 HC.861HD.392 HJ.196 HR.447 HR.781 HS.149 HC.862 HD.394 HH.699 HJ.197 HR.448 HR.789 HS.150 HD.399 HH.700 HJ.199 HR.511 HR.980 HS.153 HD. 60 HD.401 HH.714 HJ.201 HR.513 HR.981 HS.156 HD. 61 HD.404 HH.715 HJ.207 HR.520 HR.989 HD. 62 HD.413 HH.716 HJ.212 HR.527 HR.993 HD. 67 HD.414 HH.717 HJ.218 HR.528 HR.995 HD. 69 HD.421 HH.719 HJ.219 HR.529 HD. 71 HD.425 HH.720 HJ.223 HR.532 HS. 1 HD. 73 HD.427 HH.721 HR.533 HS. 5 HD. 74 HM.266 HR.535 HS. 7 INSPECTION OF DART PROPELLER SHAFTS IN INSTALLED ENGINES - SHAFTS FROM UNRECORDED INGOT POSITIONS Shaft Serial No. Shaft Serial No. Shaft Serial No. Shaft Serial No. Shaft Serial No. Shaft Serial No. Shaft Serial No. HA. 28 HA.961 HC.577 HD.840 HH.670 HJ.957 HM.398 HA. 29 HA.962 HC.578 HD.841 HH.671 HJ.958 HM.399 HA. 30 HA.963 HC.579 HD.842 HH.672 HM.400 HA. 31 HA.964 HC.580 HD.843 HH.673 HM.355 HM.401 HA. 32 HC.581 HD.844 HH.674 HM.356 HM.402 HA. 37 HB. 35 HC.582 HD.845 HH.675 HM.357 HM.403 HA. 70 HB. 36 HC.850 HD.846 HH.676 HM.358 HM.404 HA. 71 HB. 37 HC.852 HD.847 HH.677 HM.359 HM.405 HA. 72 HB. 38 HC.853 HD.848 HH.678 HM.360 HM.406 HA. 73 HB. 39 HC.855 HD.849 HH.679 HM.361 HM.407 HA. 74 HB. 40 HC.859 HD.850 HH.680 HM.362 HM.408 HA. 75 HB. 41 HC.996 HD.851 HH.681 HM.363 HM.409 HA. 76 HB.975 HD.852 HH.682 HM.364 HM.410 HA. 77 HB.976 HD.807 HH.683 HM.365 HM.411 HA. 78 HB.977 HD.808 HH.638 HH.684 HM.366 HM.412 HA. 79 HB.978 HD.809 HH.639 HH.685 HM.367 HM.413 HA. 80 HB.979 HD.810 HH.640 HH.686 HM.368 HM.414 HA. 81 HB.980 HD.811 HH.641 HH.687 HM.369 HM.415 HA. 82 HB.981 HD.812 HH.642 HH.688 HM.370 HM.416 HA. 83 HB.982 HD.813 HH.643 HH.689 HM.371 HM.417 HA. 84 HD.814 HH.644 HH.690 HM.372 HM.418 HA. 85 HC.539 HD.815 HH.645 HH.691 HM.373 HM.419 HA. 86 HC.540 HD.816 HH.646 HH.692 HM.374 HM.420 HA. 87 HC.541 HD.817 HH.647 HH.693 HM.375 HM.421 HA. 88 HC.542 HD.818 HH.648 HH.694 HM.376 HM.422 HA. 89 HC.543 HD.819 HH.649 HH.798 HM.377 HM.423 HA. 90 HC.544 HD.820 HH.650 HH.799 HM.378 HM.424 HA. 91 HC.545 HD.821 HH.651 HH.800 HM.379 HM.425 HA. 92 HC.546 HD.822 HH.652 HH.801 HM.380 HM.426 HA. 93 HC.547 HD.823 HH.653 HH.802 HM.381 HM.427 HA. 94 HC.548 HD.824 HH.654 HH.803 HM.382 HM.428 HA. 95 HC.549 HD.825 HH.655 HH.804 HM.383 HM.429 HA. 96 HC.550 HD.826 HH.656 HM.384 HM.430 HA. 97 HC.558 HD.827 HH.657 HJ.944 HM.385 HM.431 HA.592 HC.559 HD.828 HH.658 HJ.945 HM.386 HM.432 HA.595 HC.560 HD.829 HH.659 HJ.946 HM.387 HM.433 HA.690 HC.561 HD.830 HH.660 HJ.947 HM.388 HM.434 HA.952 HC.562 HD.831 HH.661 HJ.948 HM.389 HM.435 HA.953 HC.563 HD.832 HH.662 HJ.949 HM.390 HA.954 HC.564 HD.833 HH.663 HJ.950 HM.391 HR.355 HA.955 HC.565 HD.834 HH.664 HJ.951 HM.392 HA.956 HC.566 HD.835 HH.665 HJ.952 HM.393 HA.957 HC.567 HD.836 HH.666 HJ.953 HM.394 HA.958 HC.568 HD.837 HH.667 HJ.954 HM.395 HA.959 HC.569 HD.838 HH.668 HJ.955 HM.396 HA.960 HC.576 HD.839 HH.669 HJ.956 HM.397 These numbers are listed in Appendices A and B of Rolls-Royce Dart Aero Engine Service Bulletin No. Da 72-367, Revision 2, dated February 18, 1970. This supersedes Amendment 39-913, 35 F.R. 145, AD 70-2-3 as amended by Amendment 39-1056, 35 F.R. 12270. This amendment becomes effective December 7, 1970.
91-25-11: 91-25-11 EMBRAER (EMPRESA BRASILEIRA de AERONAUTICA, S.A.): Amendment 39-8167. Docket No. 91-CE-92-AD. Applicability: EMB-110 Series airplanes (all serial numbers), certificated in any category. Compliance: Required within the next 10 hours time-in-service after receipt of this AD, unless already accomplished. To prevent severe vibration, flutter, and loss of control of the airplane caused by incorrect installation of the rudder trim tab system, accomplish the following: (a) Visually inspect the rudder trim tab system for correct assembly in accordance with the instructions in EMBRAER Service Bulletin (SB) No. 110-27-0091, dated December 5, 1991. (1) If determined to be correctly installed in accordance with the criteria specified in EMBRAER SB No. 110-27-0091, return the airplane to service. (2) If determined to be incorrectly installed in accordance with the criteria specified in EMBRAER SB No. 110-27-0091, reinstall the rudder trim tab system in accordance with the instructions in EMBRAER SB No. 110-27-0091. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. (d) The inspection and possible reinstallation required by this AD shall be done in accordance with EMBRAER Service Bulletin (SB) No. 110-27-0091, dated December 5, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from EMBRAER, P.O. Box 343-CE, 12.200 Sao Jose dos Campos, Sao Paulo, Brazil; or EMBRAER Aircraft Corporation, 276 SW 34th Street, Fort Lauderdale, Florida 33315. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. (e) This amendment (39-8167, AD 91-25-11) becomes effective on February 10, 1992, as to all persons except those persons to whom it was made immediately effective by priority letter AD 91-25-11, issued 12/6/91, which contained this amendment.
2022-06-07: The FAA is superseding Airworthiness Directive (AD) 2016-09- 01, which applied to certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2016-09-01 required repetitive inspections for cracking of the left- and right-side forward outer chords of the pivot bulkhead, and related investigative and corrective actions if necessary. AD 2016-09-01 also provided a modification of the pivot bulkhead, which terminated the repetitive inspections. This AD was prompted by reports of fatigue cracking of the forward outer chord of the station (STA) 2370 pivot bulkhead, and the determination that the compliance times need to be reduced, post-modification inspections must be done, and the inspections areas need to be expanded due to additional cracking found prior to the inspection times required by AD 2016-09-01. This AD retains certain requirements of AD 2016-09-01. This AD also requires doing repetitive detailed and high frequency eddy current (HFEC) inspections of the longeron fitting, and, for post- repair and post-modification inspections, the bulkhead assembly structure, for any cracking, and doing all applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2009-04-05: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 182Q and 182R airplanes that are equipped with Societe de Motorisations Aeronautiques (SMA) Aircraft Diesel Engine (ADE) Model SR305-230-1 or Model SR305-230 converted to Model SR305-230-1 installed under Supplemental Type Certificate (STC) SA03302AT. This AD requires you to remove the intercooler and the intercooler inlet and outlet hoses, install a reworked intercooler and new intercooler inlet and outlet hoses, inspect hoses and clamp torques, repetitively inspect installation of the intercooler outlet and inlet hose assemblies for any displacement or damage of clamps or hoses, and, if necessary, replace any damaged clamps or hoses. This AD results from a report of two instances of induction hose disconnection occurring while in service, resulting in a loss of turbo boost and a significant loss of engine power. We are issuing this AD to detect and correct improper intercooler outlet and intercooler inlet hose assembly installations, which could result in loss of turbo boost and a significant loss of engine power. This failure could lead to an inability to maintain constant altitude in flight.
98-17-01: This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. TFE731 series turbofan engines, that currently requires the installation of a clamp assembly to support the rigid fuel tube. This action would require the installation of a clamp assembly to support the rigid fuel tube. This amendment requires installation of an improved flexible (flex) fuel tube. This amendment is prompted by reports of fuel leaks from a cracked fuel tube in engines that have already installed a clamp assembly in accordance with the current AD. The actions specified by this AD are intended to prevent cracking of the fuel tube and the subsequent leakage of fuel on or around electrical components, which can cause an engine fire.
78-14-09: 78-14-09 PYROTECTOR, INC.: Amendment 39-3262. Applies to P/Ns 30-207-2, -2A, and -2B; 30-207-3, -3A, and -3B; 30-207-4, -4A, and -4B; 30-207-6, -6A, and -6B; 30-207-7, and -7A; 30-207-8; 30-207-10; 30-207-19; 30-207-20A; 30-215, 30-215-4, and -4B radiation sensing type fire detectors. Compliance is required as indicated. To prevent operation of aircraft with fire detectors possibly having undetected open main power lines, accomplish the following: 1. Check the fire detection system by August 15, 1978, and every 100 hours time in service thereafter, in accordance with Chloride Pyrotector Advisory Bulletin No. PY78-1, Revision 1, dated April 7, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. NOTE: The pilot/operator may perform the required checks. NOTE: For the requirements regarding the listing of compliance and method of compliance with this AD in the aircraft's permanent maintenance record, seeFAR 91.173. 2. Replace faulty detectors with FAA approved replacement detectors. Replacement detectors must be determined to be in compliance with the certification requirements of the aircraft and approved by the FAA for installation on the model aircraft. The manufacturer's advisory bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 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 Chloride Pyrotector, 333 Lincoln Street, Hingham, Massachusetts 02043. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at FAA, New England Region Headquarters, Burlington, Massachusetts. This amendment becomes effective August 8, 1978.
2013-01-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, 737-400, 737-500, and 757-200 series airplanes. This AD was prompted by a report of damage caused by electrical arcing to the wires that connect seat electronics boxes (SEBs). This AD requires installing a new relay and doing certain wiring changes of the entertainment control switch. We are issuing this AD to prevent power from being supplied to passenger seats when the entertainment control switch is in the OFF position, which could cause an electrical shock hazard resulting in serious or fatal injury to maintenance personnel.
98-16-14: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman Ltd. (Pilatus Britten-Norman) BN-2, BN-2A, BN-2B, and BN-2T series airplanes. This AD requires replacing the attachment bolts, nuts and washers of the lower fitting of the main landing gear (MLG), and adjusting the torque values of the nuts. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the bolts that attach the lower fitting of the MLG to the nacelle from becoming threadbound, which could result in structural failure of the MLG with consequent loss of control of the airplane during takeoff, taxi, or landing operations.
98-16-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42 and ATR72 series airplanes, that requires one-time inspections to verify the correct shape of the stiffeners for the upper engine cowl and to detect wear of the aft upper fittings of the rear engine mounts, 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 prevent wear (scratches or grooving) of the aft upper fittings of the rear engine mount, and consequent reduced structural integrity of the engine mounts.
84-12-01 R1: 84-12-01 R1 HUGHES HELICOPTERS, INC. (HUGHES HELICOPTERS): Amendment 39-4877 as amended by Amendment 39-4937. Applies to Model 369D and 369E helicopters certificated in all categories. Compliance is required prior to further flight, unless already accomplished. To detect unapproved blades and prevent possible rotor blade failure in flight, accomplish the following: For Hughes Helicopters, Inc., Model 369D and 369E helicopters with main rotor blades installed which have been procured from any source. (a) To verify that the main rotor blades are of the proper Part Number (P/N) 369D21100 internal configuration, comply with the following: (1) A coin tap test or equivalent test shall be used to identify the number of ribs in each blade. Carefully tap along the length of the blade, aft of the spar, from the tip end, using a heavy coin; e.g., U.S. quarter, half dollar, or equivalent. Note the number of ribs in the blade by the difference in sound. The proper P/N 369D21100 blade has 20 ribs, 1.5 inches apart, beginning 1.5 inches from the blade tip. The unapproved 369A1100 series blade has only four ribs, beginning 3 inches from the blade tip. (2) The unapproved blade also has a painted over, flush plug installed to fill a 0.218- to 0.224-inch-diameter hole required in the trailing edge inboard end of all 369A1100 series blades. There is no such hole in the proper P/N 369D21100 blades. Inspect the blade for a filled hole in the trailing edge inboard end. (b) If a blade has four ribs and a filled hole, an improper blade is installed. Replace with an airworthy proper P/N 369D21100 blade prior to further flight. (c) Alternative inspections, modifications, or other actions which provide an equivalent level of safety to this AD may be used when approved by the Manager, Western Aircraft Certification Office, Hawthorne, California. The procedure specified in Hughes Service Information Letter DL-57 or EL-5, dated February 10, 1984, is an alternative. NOTE: Hughes Service Information Letter No. DL-57 or EL-5 dated February 10, 1984, pertains to identification of improper blades. Amendment 39-4877 became effective June 11, 1984. This Amendment 39-4937 becomes effective October 24, 1984.
2012-25-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-200B, 747-200C, 747-200F, 747- 300, 747-400, 747-400F, and 747SR series airplanes. This AD was prompted by reports of broken and damaged latch pin retention bolts and subsequent migration of the latch pins of the main deck side cargo door (MDSCD). This AD requires various repetitive inspections of the MDSCD latch pin fittings, measuring the latch pin, and related investigative and corrective actions if necessary. This AD also requires modifying the latch pin fittings and installing new latch pins and latch pin fasteners. We are issuing this AD to prevent loss of the cargo door and rapid depressurization of the airplane.
98-16-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a one-time inspection for cracking of the rear pressure bulkhead; and installation of a reinforcement angle on the rear pressure bulkhead; or repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracking of the rear pressure bulkhead, which could result in sudden loss of cabin pressure and the inability to withstand fail-safe loads.
84-23-03: 84-23-03 ALEXANDER SCHLEICHER: Amendment 39-4945. Applies to Model ASK-21 sailplanes, all serial numbers, certificated in any category. Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To comply with the requirements of Federal Aviation Regulation 21.29(a)(3), accomplish the following: 1. Remove the one placard in the German language fitted in the front and rear cockpit, and replace with new placards in the English language, in accordance with Alexander Schleicher ASK-21 Technical Note No. 14, dated May 16, 1984. 2. Remove and replace the following manual pages in accordance with Alexander Schleicher ASK-21 Technical Note No. 14, dated May 16, 1984: a. In the Flight Manual, remove pages 2 (December 20, 1983) and 21 (March 9, 1983), and replace with pages 2 (May 16, 1984) and 21 (May 16, 1984). b. In the Instructions for Continued Airworthiness, remove pages 2 (December 20, 1983) and 59 (March 9, 1983), and replace with pages 2 (May 16, 1984) and 59 (May 16, 1984). 3. Paragraph 2 of this AD may be accomplished by the pilot with logbook entry. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-10O, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium, telephone 513.38.30 extension 2710. The Alexander Schleicher ASK-21 Technical Note No. 14, dated May 16, 1984, identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 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 Alexander Schleicher Segelflugzeubau, D-6416 Poppenhausen, Federal Republic of Germany. These documents may also be examined at the Office of the Regional Counsel, 12 New EnglandExecutive Park, Burlington, Massachusetts 01803. This amendment becomes effective on November 14, 1984.
98-16-25: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) airplanes, that currently requires repetitive inspections to detect discrepancies of the shock strut end caps and attachment pins of the main landing gear (MLG), and replacement of discrepant parts with new parts. It also requires a check for and replacement of certain pins that currently may be installed on some airplanes. This amendment adds a requirement for the installation of new, improved MLG shock strut upper and lower attachment pins, which constitutes terminating action for the repetitive inspections. This amendment also reduces the applicability of the existing AD by removing certain airplanes. 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 failure of attachment pins andthe attachment pin end caps, which could result in failure of the MLG.
98-16-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires repetitive inspections to detect corrosion or plating cracks of the pin assemblies in the forward trunnion support of the main landing gear (MLG), and replacement of the pin assembly with a new assembly, if necessary. Such replacement, if accomplished, constitutes terminating action for the repetitive inspections. This amendment is prompted by reports indicating that these pin assemblies were found to have corroded as a result of plating cracks. The actions specified by this AD are intended to detect and correct such corrosion and plating cracks, which could cause breakage of these assemblies, and consequent collapse of the MLG.
2012-27-01: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Tay 620-15 turbofan engines. This AD requires a one-time inspection of the low-pressure compressor (LPC) fan blades and if erosion is found their replacement before further flight. This AD was prompted by evidence of excessive leading edge erosion of the LPC fan blades on certain Tay 620-15 engines. We are issuing this AD to prevent failure of the LPC fan blade, which could result in uncontained engine failure and damage to the airplane.
66-19-03: 66-19-03 MARTIN: Amdt. 39-272 Part 39 Federal Register August 10, 1966. Applies to Model 404 Airplanes. Compliance required as indicated. To detect cracks in the main landing gear oleo cylinders, accomplish the following: (a) Inspect main landing gear oleo cylinders, Martin P/N SE997712, in accordance with (c) within the next 50 hours' in service after the effective date of this AD, unless already accomplished within the last 100 hours' time in service, and at intervals not to exceed 150 hours' time in service from the last inspection. (b) Inspect main landing gear oleo cylinders, except Martin P/N SE997712, in accordance with (c) within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. (c) Remove all grease, dirt, and loose paint in the area between the jury strut attach lugs of the right and left main landing gear oleo cylinders, and inspect each of these areas for cracks using an ultrasonic method or an FAA-approved equivalent method. (d) If a crack is found during the inspection specified in (c), replace the cylinder with a part of the same part number inspected in accordance with this AD and found free of cracks or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, before further flight except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. (e) 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 (a) to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This directive effective August 19, 1966.
98-16-03: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Models TB9 and TB10 airplanes. This AD requires repetitively inspecting the wing front attachments on the wing and fuselage sides for cracks, and repetitively incorporating a certain modification kit (type of kit and time of incorporation depends on whether cracks are found during the inspection). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent structural failure of the wing front attachments caused by fatigue cracking, which could result in the wing separating from the airplane if the airplane is operated with cracked wing front attachments over an extended period of time.
92-08-15: 92-08-15 MOONEY AIRCRAFT CORPORATION: Amendment 39-8266. Final copy of priority letter. Docket No. 92-CE-29-AD. Applicability: Model M20J airplanes, serial numbers 24-3201, 24-3218 through 24-3238, 24-3240 through 24-3250, and 24-3252 through 24-3256, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent rudder imbalance, which could lead to aerodynamic problems and loss of control of the airplane, accomplish the following: (a) Prior to further flight after the effective date of this AD, accomplish the following: (1) Fabricate a placard with the words "Maximum Gross Weight Reduced to 2,740 Pounds." Install this placard on the airplane instrument panel within the pilot's clear view. (2) Insert a copy of this AD into the limitations section of the Airplane Flight Manual and operate the airplane accordingly. (b) Within the next 15 hours time-in-service after the effective date of this AD, inspect the airplane to ensure that the rudder static balance is within the required limits in accordance with paragraphs 1. through 3. of the INSTRUCTIONS section of Mooney Aircraft Corporation Service Bulletin (SB) M20-252, dated April 6, 1992. (c) If the rudder static balance falls outside the limits specified in Mooney Aircraft Corporation SB M20-252, prior to further flight, adjust the rudder balance weight in accordance with paragraphs 4. through 7. of the INSTRUCTIONS section of Mooney Aircraft Corporation SB M20-252, dated April 6, 1992. (d) The placard and Airplane Flight Manual limitation required by paragraphs (a)(1) and (a)(2) of this AD are no longer required after compliance with paragraphs (b) and (c) of this AD as applicable. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, 4400 Blue Mound Road, Fort Worth, Texas 76193-0150. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Airplane Certification Office. (f) The inspection and possible modification required by this AD shall be done in accordance with Mooney Aircraft Corporation Service Bulletin M20-252, dated April 6, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Mooney Aircraft Corporation, P.O. Box 72, Kerrville, Texas 78029-0072. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room8401, Washington, DC. (g) This amendment becomes effective on June 30, 1992, to all persons except those persons to whom it was made immediately effective by priority letter AD 92-08-15, issued April 9, 1992, which contained the requirements of this amendment.