Results
98-24-31: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-24-31, which was sent previously to all known U.S. owners and operators of BHTC Model 430 helicopters by individual letters. This AD requires, within 10 hours time-in-service (TIS), inspecting the lateral control tube (control tube) assembly and the forward fairing assembly for chafing. If chafing is found, replace the control tube assembly and rework the forward fairing assembly before further flight. If no chafing is found during the initial inspection, perform the corrective actions within the next 150 hours TIS. This amendment is prompted by two incidents of binding of the control tube assembly that occurred during flight. The actions specified by this AD are intended to prevent binding of the control tube assembly with the inside surface of the forward fairing assembly under certain load conditions and subsequent loss of control of the helicopter.
97-23-03: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model HS 748 series airplanes. This action requires a one-time visual inspection of the retraction jack mounting brackets in the nose landing gear bay to determine the type of attachment bolts installed on the bracket bearing caps, and replacement of any incorrect bolt with a serviceable bolt of the correct type. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the bearing cap attachment bolts, which could result in detachment of the bearing caps and consequent collapse of the nose landing gear on landing.
2005-12-06: The FAA is superseding an existing airworthiness directive (AD) for Teledyne Continental Motors (TCM) (formerly Bendix) S-20, S- 1200, D-2000, and D-3000 series magnetos equipped with impulse coupling assemblies. That AD currently requires replacing riveted-impulse coupling assemblies and snap-ring coupling assemblies, which are worn beyond limits, with serviceable riveted-impulse coupling assemblies or snap-ring impulse coupling assemblies. This ad requires a reduced inspection interval for magnetos with riveted-impulse coupling assemblies installed on certain Lycoming engine models. This AD does not lower the inspection interval for magnetos with snap-ring impulse coupling assemblies. This AD also limits the applicability to certain Lycoming engine models. This AD results from data provided by the manufacturer that shows a need to reduce the inspection intervals for riveted-impulse coupling assemblies used on certain Lycoming engine models. We are issuing this AD to preventfailure of the magneto impulse coupling assembly and possible engine failure. DATES: This AD becomes effective July 19, 2005. The Director of the Federal Register previously approved the incorporation by reference of certain publications as listed in the regulations as of July 18, 1996 (61 FR 29934, June 13, 1996).
2018-04-13: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. AS907 series turbofan engines. This AD was prompted by seven loss-of-thrust-control events attributed to water intrusion of the engine electronic control unit (ECU). This AD requires applying sealant to identified areas of the ECU and requires inserting a copy of certain airplane operating procedures into the applicable flight manuals. We are issuing this AD to address the unsafe condition on these products.
2018-01-12 R1: We are revising airworthiness directive (AD) 2018-01-12 for Airbus Helicopters Model AS350B3 helicopters to correct an error. As published, AD 2018-01-12 referenced an incorrect monostable toggle switch part number (P/N) in the preamble and regulatory text. This document corrects the error. In all other respects, the original document remains the same.
81-21-06: 81-21-06 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-4226. Applies to all Model SA 330 series helicopters certificated in all categories. (Airworthiness Docket No. 81-ASW-42.) Compliance is required within 50 hours' time in service after the effective date of this AD, unless already accomplished. To ensure bearing lubrication and to prevent balls escaping from each main rotor blade lever assembly eyebolt pivot ball bearing, accomplish the following: (a) Applies to main rotor heads P/N 330A.31.0020 and 330A.31.0030, all dash numbers, not modified to AMS 07.43.008. Incorporate modification AMS 07.43.008 as described in paragraph 2, Accomplishment Instructions, of SNIAS Service Bulletin No. 65.30, dated November 20, 1979, or FAA approved equivalent. (b) Applies to main rotor heads P/N 330A.31.0020 and 330A.31.0030, all dash numbers, not modified to AMS 07.43.028. Incorporate modification AMS 07.43.028 as described in paragraph 2, Accomplishment Instructions, of SNIAS Service Bulletin No. 65.38, dated July 4, 1980, or FAA approved equivalent. (c) Applies to main rotor heads P/N 330A.31.0000.05 to .18 inclusive not modified to AMS 330A.07.43.038, and main rotor heads 330A.31.0020.00 to .04 inclusive not modified to AMS 330A.07.43.037, and main rotor heads P/N 330A.31.0030.00 to .03 inclusive not modified to AMS 330A.07.43.037. Inspect in accordance with paragraph C, Description, of SNIAS Service Bulletin No. 01.33, dated March 31, 1981, or FAA approved equivalent. Before further flight, replace bearings which are not fitted with sealing flange retaining ring, with serviceable bearings having the same MRC part number, that are fitted with the sealing flange retaining ring, or with serviceable bearings manufactured by FAFNIR, or with an FAA approved equivalent bearing. (d) Equivalent means of compliance with this AD must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o American Embassy, Brussels Belgium. This amendment becomes effective October 12, 1981.
61-24-03: 61-24-03 DOUGLAS: Amdt. 371 Part 507 Federal Register November 23, 1961. Applies to All DC-8 Aircraft, Serial Nos. 45252-45289, 45291-45306, 45376-45393, 45408-45413, 45416-45419, 45421-45431, 45433-45437, 45442-45445, 45526, 45565-45570, 45588-45606, 45609-45614, 45616-45628, 45636. \n\n\tCompliance required within 1,000 hours' time in service after the effective date of this AD, but in no event later than February 28, 1962. \n\n\tTo prevent inadvertent application of forward thrust when reverse thrust is desired under emergency conditions, the following modification shall be accomplished: \n\n\tIncorporate a throttle-thrust brake interlock system which will: \n\n\t(a)\tPrevent application of reverse thrust until the reverse buckets are in the reverse thrust position, and \n\n\t(b)\tReturn a throttle to the detent position should the corresponding buckets move from the reverse thrust position. \n\n\tThe modification shall be accomplished in accordance with technical data approved by theChief, Engineering and Manufacturing Branch, FAA Western Region. \n\n\t(Douglas DC-8 Service Bulletin Nos. 78-48, 78-50, 78-51 and 78-52 for DC-8 aircraft equipped with JT3C6, JT3D-1, JT4A and Rolls Royce RCO-12 engines, respectively, pertain to this same subject and describe particular FAA approved means of compliance with this AD.) \n\n\tWhen the above modification is accomplished, compliance with the provisions of AD 61-21-02 is no longer required. \n\n\tThis directive effective November 23, 1961.
98-20-34: This amendment adopts a new airworthiness directive (AD) that applies to Twin Commander Aircraft Corporation Models 500, 500-A, 500-B, 500-S, 500-U, 520, 560, 560-A, 560-E, 560-F, 680, 680-E, 680FL(P), 680T, 680V, 680W, 681, 685, 690, 690A, 690B, 690C, 690D, 695, 695A, 695B, and 720 airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potentialhazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2018-03-05: We are adopting a new airworthiness directive (AD) for various aircraft equipped with a BRP-Rotax GmbH & Co. KG (formerly BRP- Powertrain GmbH & Co. KG; Bombardier-Rotax GmbH & Co. KG; Bombardier- Rotax GmbH) 912 A series engine. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as defective valve push-rod assemblies manufactured from June 8, 2016, through October 2, 2017. We are issuing this AD to require actions to address the unsafe condition on these products.
99-02-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes. This amendment requires repetitive tests to detect internal leakage of hydraulic fluid within the hydraulic components of the ground spoiler system and to detect a buildup of pressure in the return line of the bypass valve, and corrective action, if necessary; installation of additional hydraulic lines and an additional hydraulic shutoff valve in the ground spoiler system; and replacement of the valve block of the ground spoiler system with a new part. This amendment also requires eventual replacement of the relief restrictor valves of the ground spoiler system with redesigned parts, which constitutes terminating action for the repetitive tests. 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 the ground spoilers from unlocking and deploying during takeoff or in flight, and consequent reduced controllability of the airplane.
2018-03-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes; Model CL-600-2D15 (Regional Jet Series 705) airplanes; Model CL-600-2D24 (Regional Jet Series 900) airplanes; and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report of rudder yoke components that had not been properly inspected at the supplier. This AD requires replacement of the left and right rudder yoke assemblies. We are issuing this AD to address the unsafe condition on these products.
85-06-06: 85-06-06 BRITISH AEROSPACE: Amendment 39-5023. Applies to Model 3101 Jetstream (all serial numbers) airplanes, certificated in any category. Compliance: Required within 100 hours time-in-service after the effective date of this AD, unless already accomplished. To assure adequate emergency lighting system power pack charge for lighting during emergency airplane evacuation, accomplish the following: (a) Incorporate British Aerospace (BAe) Modification JM7431 in accordance with the instructions contained in BAe Alert Service Bulletin No. 33-A-JM7431, Revision 1, dated October 7, 1984. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) 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 May 8, 1985.
85-23-03: 85-23-03 LOCKHEED: Amendment 39-5156. Applies to Lockheed Models 382, 382B, 382E, 382F, and 382G series Hercules airplanes with Lockheed serial numbers 4134, 4147, 4208, 4248, 4250, 4299, 4300, 4301, 4303, 4362, 4383, 4384, 4388, 4391, 4472, 4477, 4558, 4561, 4565, 4586, 4590, and 4763. CAUTION: The fire extinguisher squibs are similar to a pistol cartridge. The squibs contain an explosive charge which could cause injury or death if accidentally fired. Do not expose squibs to heat or an electric current or strike or drop squibs. Failure to comply may result in serious injury or death to personnel. Compliance is required within 30 days after the effective date of this AD, unless already accomplished. To preclude misfiring of fire extinguisher systems, accomplish the following: A. Inspect each fire extinguisher squib (two per airplane) in accordance with Lockheed Alert Service Bulletin A382-26-4 dated October 4, 1984, to determine part number and loading date.Squibs having Holex part number 4199-1 (Lockheed number 695679-15), and having a loading date of 1/84, must be replaced with a serviceable squib prior to further flight, except as provided in paragraph B., below. B. If a serviceable replacement squib is not available, a part number 4199-1 squib having a loading date of 1/84 may be used during the interim, provided the following is accomplished: (1) Make a resistance measurement of the squib in accordance with applicable maintenance instructions of Lockheed Alert Service Bulletin A382-26-4, dated October 4, 1984, before the aircraft is returned to service, and every 30 days thereafter, until an acceptable replacement squib has been installed or until the squib reaches its life limit, whichever occurs first. (2) Ensure that the resistance measurement is, and remains at each 30 day check, within the tolerances specified in the applicable maintenance instructions referred to in Lockheed Alert Service Bulletin A382-26-4,dated October 4, 1984. C. Special 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. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. All persons affected by this directive who have not already received the applicable service bulletin from the manufacturer may obtain copies upon request to Lockheed-Georgia Company, Field Service Office, 86 South Cobb Drive, Marietta, Georgia 30063. These documents may be examined at FAA, Central Region, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia, or FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington. This amendment becomes effective on November 24, 1985.
61-24-01: 61-24-01 BOEING AND DOUGLAS: Amdt. 369 Part 507 Federal Register November 23, 1961. Applies to all 707/720 Series and DC-8 Series aircraft equipped with Pratt & Whitney Aircraft JT3C-12, JT3D-1, JT3D-1-MC6, JT3D-1-MC7, and JT3D-3 engines. \n\n\tCompliance required as indicated. \n\n\tA recent failure of the low compressor turbine shaft resulted in overspeeding and separation of the low compressor turbines. To prevent recurrence of this difficulty, the following action is required on any turbine engine that has been disassembled since last overhaul to the extent of exposing any bearing compartment: \n\n\tAt periods not to exceed 12 hours' time in service, the main oil screen shall be disassembled, inspected and cleaned in accordance with Pratt and Whitney Overhaul Manual. The inspection shall be repeated until the screen is free of contamination for two successive inspections. If contaminants indicative of engine part failure or contaminants in sufficient quantity to plug the oil screen are found during any inspection the engine shall not be operated until the cause of the difficulty has been determined and satisfactorily corrected. \n\n\tUpon 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. \n\n\t(Pratt and Whitney telegram to all turbojet engine operators dated November 9, 1961, covers the same subject.) \n\n\tThis directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated November 10, 1961. \n\n\tRevised February 13, 1962, and June 7, 1962.
2018-03-10: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-300 series airplanes. This AD was prompted by reports of scribe line damage on fuselage skin. This AD requires detailed inspections of fuselage skin for the presence of scribe lines, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
88-17-01: 88-17-01 ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORPORATION (ALLISON): Amendment 39-6092. Final copy of Priority Letter AD 88-17-01 issued August 15, 1988. Applicability: Allison Model 250-B17, -C20, -C20R, and -C30 series engines, incorporating Bendix gas producer fuel controls listed in the attached appendix, installed in aircraft certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent possible engine over-temperature, loss of throttle response, or unscheduled power increase accomplish the following: (a) Remove from service within the next ten (10) operating hours after the effective date of this AD, the affected Bendix gas producer fuel controls listed by part number and serial number in the attached appendix and replace with a serviceable part. NOTES: (1) Out-of-service affected Bendix gas producer fuel controls, listed by part number and serial number in the attached appendix, may be returned to serviceupon the incorporation of Allison Alert Commercial Engine Bulletin (CEB) titled "Engine, Fuel and Control, Inspection of Certain Bendix Fuel Control Bellows Assemblies", dated August 1, 1988, with applicability as follows: ENGINE MODEL BULLETIN NUMBER 250-C20 Series CEB-A-1272 250-B17 Series TP CEB-A-1231 250-C30 Series CEB-A-73-3042 250-C20R Series CEB-A-73-4008 (2) Those affected Bendix gas producer fuel controls incorporating the above-cited Allison Alert CEB are identified by a green mark on the cylinder portion of the self-locking cap nut and either the letter "A" or the letter "B" in the "LESS ISSUE" block of the data plate. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where this AD can be accomplished. (c) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Chicago Aircraft Certification Office, may adjust the compliance time specified in this AD. Allison Alert CEB titled "Engine, Fuel and Control, Inspection of Certain Bendix Fuel Control Bellows Assemblies", dated August 1, 1988, identified and described in this document, 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 this document from the manufacturer may obtain copies upon request to Allison Gas Turbine Division, General Motors Corporation, P.O. Box 420, Indianapolis, Indiana 46206-0420. This document may also be examined at the Office of the Assistant Chief Council, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 88-ANE-32, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment (39-6092, AD 88-17-01) becomes effective March 1, 1989, as to all persons except those persons to whom it was made immediately effective by individual Priority Letter AD 88-17-01 issued August 15, 1988, which contained this amendment. APPENDIX AD 88-17-01 Bendix Fuel Controls: Bendix Part No.: 2524644-26 (Allison 23033917) Serial No.: 87241174 87490092 88041524 88090122 87370001 88041515 88090107 88090124 * 87430041 88041516 88090110 88090125 87430042 88041517 88090112 88090126 * 87430044 88041518 88090114 88090128 87430045 88041519 88090116 88090129 87490081 88041520 88090118 88090130 87490082 88041521 88090119 88090131 87490083 88041522 88090120 87490084 88041523 88090121 Bendix Part No.: 2524654-23 (Allison 23036660) Serial No.: 87251235 87460078 Bendix Part No.: 2524886-10 (Allison 23033919) Serial No.: 87430052 87430055 87490102 87430053 87490101 87490104 Bendix Part No: 2524922-6 (Allison 23033849) Serial No.: 87370010 88090143 88090144 Bendix Part No.: 2524957-3 (Allison 23030614) Serial No.: 84250105 Bendix Part No.: 2524986-2 (Allison 23038954) Serial No.: 87490095 87490098 Bendix Part No.: 2549032-2 (Allison 23037275) Serial No.: 87430056 87430063 88090154 88090163 87430057 87430065 88090155 88090165 87430059 88090147 88090156 88090166 87430060 88090149 88090157 88130236 87430061 88090151 88090158 88130249 87430062 88090152 88090160 88130250 *These Serial Nos. corrected from Priority Letter AD 88-17-01 by this Final Rule.
86-15-09: 86-15-09 GROB-WERKE GMBH: Amendment 39-5356. Applies to Model Grob G 109B motorgliders (serial numbers 6200 through 6430 inclusive) certificated in any category. Compliance is required as indicated, unless already accomplished. To prevent the possibility of encountering aileron flutter which could result in the loss of control of the motorglider, accomplish the following: (a) Within the next 5 hours time-in-service after the effective date of this AD: (1) Attach a placard on the instrument panel adjacent to the airspeed indicator with the following wording: "NEVER EXCEED AIRSPEED (IAS): 190 km/h (100 kts)." (2) Place a copy of this AD in the limitation section of the flight manual. (b) Modification of the motorglider, by installing a rudder damper, additional mass- balance to the ailerons, and stiffening the upper and lower rudder hinge attachment points on the vertical tail, in accordance with the "Instructions" section of GROB-Werke GmbH Technical Information No. TM 817-20 dated Jan. 29, 1986, and GROB-WERKE GmbH Repair Instruction No.'s 817-20/1, 817-20/2, 817-20/3, dated Jan. 29, 1986, deletes the requirement for compliance with Paragraph (a). Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 15 Rue de la Loi, B-1040 Brussels, Belgium, telephone no. 513.38.30 ext. 2710 or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, telephone no. 516-791-6680. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD.Grob-Werke GmbH Technical Information No. 817-20, dated Jan. 29, 1986, and Grob- Werke GmbH Repair Instructions Nos. 817-20/1, 817-20/2, 817-20/3, dated Jan. 29, 1986, identified and described in this document, are 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 Grob Systems Inc., Aircraft Division, I-75 and Airport Drive, Bluffton, Ohio 45817. These documents also may be examined at the Office of Regional Counsel, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket 86-ANE- 29, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on July 31, 1986.
61-22-01: 61-22-01 BELL: Amdt. 361 Part 507 Federal Register November 7, 1961. Applies to All Model 47 Series Helicopters. Compliance required as indicated. To preclude failure of the main rotor pitch link rod end bearing P/N RE4F7 which causes loss of main rotor control, the following one-time only inspection is required to determine that the bearing is correctly installed. (a) Within the next 10 hours' time in service after the effective date of this AD, on all Model 47 Series helicopters, inspect the main rotor control pitch link located between the stabilizer bar mixing lever and the main rotor blade control horn to see that the rod end bearing sides are parallel to the clevis slot. These surfaces must be adjusted parallel to prevent binding of the rod end bearing at extreme ends of travel, as specified in all applicable model maintenance manuals. (b) Within the next 10 hours' time in service after the effective date of this AD, inspect all Models 47D, 47D-1, 47H-1, 47G, 47G-2, and 47J helicopters equipped with Fafnir P/N RE4F7 rod end bearing as follows: (1) Remove the RE4F7 rod end bearing in accordance with the applicable maintenance manual and visually inspect for obvious damage or defect of the outer race such as nicks and gouges adjacent to the shield, looseness, roughness, distortion or kinks in bearing shields. (2) If any damage or defect is found, replace the bearing prior to further flight. (3) If no damage or defect is found, the bearing may be reinstalled. (4) The installation of the bearings under subparagraphs (2) or (3) shall be made in accordance with the applicable maintenance manual making positive that requirements of paragraph (a) are followed. (c) Helicopters listed in paragraph (b) that are not equipped with the Fafnir P/N RE4F7 bearings are equipped with Bell P/N 47-140-241-3 rod end bearings. These bearings are of a different make and only require the inspection called for in paragraph (a).(Bell Service Instruction 345 SI covers this same subject for the models listed under (b)). This directive effective November 7, 1961.
61-23-04: 61-23-04 DOUGLAS: Amdt. 363 Part 507 Federal Register November 7, 1961. Applies to All Models DC-6, DC-6A, and DC-6B Aircraft Serial No. 42854 Up To and Including Serial No. 44429. \n\n\tCompliance required as indicated. \n\n\tSeveral Instances have been reported of spanwise cracks found in the center wing, front spar lower outboard cap. The cracks were approximately 3 inches in length and were located on the aft side of the spar cap body just outboard of the landing gear fitting (Station 163 approximately). Instances have also been reported where cracks have progressed forward into adjacent bolt holes. As a result of the foregoing, the following must be accomplished on the affected area of lower front spar caps having in excess of 15,000 hours' time in service unless the affected area has already been reworked, repaired or replaced as specified in paragraphs (b), (c), or (d). \n\n\t(a)\tWithin the next 3,000 hours' time in service, accomplish a dye penetrant inspection or equivalent for cracks in the aft tang of the outboard front spar lower cap for a spanwise distance of 5 inches from the inboard end (Station 163 approximately) and rework in accordance with (b), (c), or (d), as required. \n\n\t(b)\tIf no cracks are detected by the inspection prescribed in (a), the area must be reworked as necessary prior to further flight per Item 4(a) of Section I of Douglas Service Bulletin No. 802, reissued October 21, 1960. \n\n\t(c)\tIf, during the inspection prescribed in (a), cracks are detected which exceed 3 inches in length along the radius of the aft tang or extend forward beyond the end bolt holes, the spar cap must be replaced prior to further flight except ferry flight in accordance with the provisions of CAR 1.76. When installing a replacement spar cap, the rework specified in Item 4(a) of Section I of Douglas Service Bulletin No. 802 reissued October 21, 1960, or equivalent, must be incorporated. \n\n\t(d)\tIf, during the inspection prescribed in (a), cracks are detected which do not exceed the limits set forth in (c), replacement of the spar cap is optional. If replaced, the rework instructions specified in (c) must be incorporated. If not replaced, the spar cap must be repaired and inspected per Section II of Douglas Service Bulletin No. 802, reissued October 21, 1960, or equivalent, prior to further flight except ferry flight in accordance with the provisions of CAR 1.76. \n\n\t(Douglas Service Bulletin No. 802, reissued October 21, 1960, covers the same subject.) \n\n\tThis directive effective December 7, 1961.
99-23-23: This amendment adopts a new airworthiness directive (AD) applicable to Bell Helicopter Textron, Inc. (BHTI) Model 412, 412EP, and 412CF helicopters. This action requires inspecting and measuring the thickness of certain main rotor yoke assemblies. This AD also requires adding 500 hours time-in-service (TIS) to the total time for main rotor yoke assemblies that measure below 0.478-inch thickness and noting the measurement and added TIS on the component history card or equivalent record. This amendment is prompted by a report of an emergency landing due to severe main rotor vibration on a BHTI Model 412 helicopter. Subsequent fatigue analysis indicates that the main rotor yoke assembly (yoke) does not have the anticipated service life when manufactured below 0.478-inch thickness. The actions specified in this AD are intended to prevent a fatigue failure of the yoke, loss of a main rotor blade, and subsequent loss of control of the helicopter.
61-23-03: 61-23-03 DE HAVILLAND: Amdt. 358 Part 507 Federal Register November 2, 1961. Applies to All Heron Model 114 Aircraft Without Modification No. 1454. Compliance required as indicated. (a) Cases have occurred of cracking of the wing rear false spar web adjacent to the wing-to-fuselage attachment P/N 14W253/4. To preclude failure of the spar, an X-ray or visual inspection for cracks must be conducted in accordance with de Havilland Technical News Sheet CT(114) No. W.10 Issue 2, within the next 250 hours' time in service after the effective date of this directive and at each 600 hours' time in service thereafter. If cracks are found, repair in accordance with de Havilland Drawing RD14W 224, Issue 4, or subsequent, within the time in service given in paragraphs (1), (2), and (3). (1) Cracks less than 1/2 inch in length must be repaired at the next wing removal and the inspection in (a) must be made every 600 hours' time in service in the interim between the inspection and the wing removal. (2) Cracks of 1/2 inch to 1 1/2 inches in length must be repaired within 300 hours' time in service after the inspection. (3) Cracks exceeding 1 1/2 inches in length must be repaired within the next 150 hours' time in service after the inspection. (b) The special inspection in (a) is no longer required when the repair per Drawing RD 14W 224, Issue 4, or subsequent, has been incorporated. (de Havilland Technical News Sheet CT(114) No. W.10 Issue 2 dated July 24, 1961, covers this subject.) This directive effective December 4, 1961.
85-17-08: 85-17-08 SIKORSKY AIRCRAFT: Amendment 39-5196. Applies to Model S-58A, B, C, D, E, F, G, H, J, BT, DT, ET, FT, HT, and JT helicopters certificated in any category and CH- 34 series HH-34 series, SH-34 series, UH-34 series, and VH-34 series helicopters certificated in the restricted category. Compliance is required as indicated, unless already accomplished. To prevent the separation of the stationary star and rotating star, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 25 hours time in service from the last inspection, visually inspect the 12 main rotor head star assembly retainer bolts, Part Number lP/N) MS20074-04-04 or P/N AN74A4, for damage and for security of fastening in accordance with Section 2, Paragraph A, of Sikorsky Alert Service Bulletin (ASB) No. 58B10-19, dated May 31, 1985, or later FAA-approved revision. (b) If damaged or loose bolts are found, fluorescent magnetic particle inspect the bolts for cracks and visually inspect the bolt threads for crossed, stripped, or flattened threads in accordance with Section 2, Paragraph A, of Sikorsky ASB No. 58B10-19, dated May 31, 1985, or later FAA-approved revision. (c) If a cracked bolt is found, or if the bolt threads are crossed, stripped, or flattened, replace with a new (zero time) bolt prior to further flight in accordance with Section 2, Paragraph A, of Sikorsky ASB No. 58B10-19, dated May 31, 1985, or later FAA-approved revision. (d) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished within the last 1,000 hours time in service, replace the 12 main rotor head star assembly retainer bolts with new (zero time) bolts in accordance with Section 2, Paragraphs A(7)(c), (d), and (e) and Paragraph B, of Sikorsky ASB No. 58B10-19, dated May 31, 1985, or later FAA-approved revision; thereafter, install new (zero time) main rotor head star assembly retainer bolts at intervals not to exceed 1,100 hours time in service. (e) Render unairworthy any bolts removed in accordance with the requirements of paragraph (d) of this AD by crushing the threads. (f) Aircraft may be ferried in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the AD can be accomplished. (g) An alternate method of compliance or adjustments of the compliance time which provide an equivalent level of safety may be used when approved by the Manager, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone number (617) 273-7118. The manufacturer's specifications and procedures identified and described in this directive are 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 Sikorsky Aircraft Division, United Technology Corporation, North Main Street, Stratford, Connecticut 06601. These documents also may be examined at the Rules Docket, Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective January 13, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD No. 85-17-08, issued August 30, 1985, which contained this amendment.
61-22-08: 61-22-08 SUD AVIATION: Amdt. 354 Part 507 Federal Register October 28, 1961. Applies to All Model SE 3130 Alouette II Helicopters. Compliance required as indicated. To remove defective bolts and preclude the possibility of further failure of the tail rotor gear box housing attachment the following inspections are required: (a) The tail rotor gear box attachment bolts P/N 66.20.043 and tail rotor gear box guides P/N 66.20.213 shall be inspected within the next 10 hours' time in service in accordance with paragraphs (d) and (e) unless this inspection has already been complied with and/or the bolts replaced with parts that comply with paragraphs (d) and (e) subsequent to August 25, 1961. (b) Every 50 hours' time in service subsequent to the completion of inspection prescribed in paragraph (a), reinspect and check the torque of the bolts and nuts P/N 66.20.043. The torque should be between 10.1 and 12.3 ft. lbs. If the bolts and nuts do not meet the torque requirements, remove the tail rotor gear box and inspect in accordance with paragraphs (d) and (e). (c) Every 100 hours' time in service subsequent to completing inspection of paragraph (a), remove the tail rotor gear box and inspect the bolts and guides in accordance with paragraphs (d) and (e). (d) The bolts P/N 66.20.043 are to be checked for cracks, corrosion, peeling and surface finish. Surface finish inspection is applicable to paragraph (a) only. Remove the zinc chromate protective finish, if applicable, by using paint remover. The diameter of the bolt bearing area at the head and at the thread end shall be measured in two directions 90 degrees apart in order to detect any out of round condition. These diameters shall not be less than 8.29 mm. (0.326 inch). The surface finish of the central necked down area and the radius at each end shall be as follows: (1) The radius shall not be less than 1.61 mm. (0.0630 inch). (2) The maximum permissible surface roughnessshall not exceed 1 micron (39 micro-inches). (3) Localized defects no greater than 50 microns deep (1950 micro-inches) are permissible. If these standards are not met the bolts shall be replaced with bolts that do meet the standards. (e) Check the bore of the three tail rotor gear box guides P/N 66.20.213 by measuring the bore along two directions 90 degrees apart. The bore dimension shall not exceed 8.33 mm. (0.328 inch). If these standards are not met the tail rotor gear box shall be replaced with a new or overhauled unit or the gear box returned to the factory or approved overhaul agency for installation of new guides before reinstallation on the helicopter. (Sud Maintenance Manual Vol. I, Chapter 5, Pages 3 and 7, and Sud Service Bulletin No. 66-11-206 cover the same subject.) This directive effective October 28, 1961.
2018-02-15: We are superseding Airworthiness Directive (AD) 2007-08-06 for British Aerospace Regional Aircraft Models HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the need for airworthiness limitations for critical components in the main and nose landing gear assemblies. We are issuing this AD to require actions to address the unsafe condition on these products.
2018-02-02: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, AS355NP, EC130B4, and EC130T2 helicopters. This AD requires inspecting the main rotor (M/R) mast jet oil lubrication hose (oil hose). This AD is prompted by a report of a blocked oil hose. The actions of this AD are intended to prevent an unsafe condition on these helicopters.