Results
81-12-06 R1: 81-12-06 R1 BENDIX: Amendment 39-4249. Applies to Bendix Engine Products Division D-3000 and D-3200 (Blue) series magnetos identified as follows, unless previously identified by the letter "X", on the upper left area of magneto data plate: a. D-3000 series (see models specified under "MAGNETO IDENTIFICATION") pressurized (dark blue) magnetos with serial numbers below 1423, installed on AVCO Lycoming TIO, LTIO-540-J2BD engines. MAGNETO IDENTIFICATION MODEL PART NO. D6LN-3200 10-682910-13 D6RN-3200 10-682910-18 These magnetos are installed on but not limited to the following aircraft engines or aircraft engine/aircraft combinations: AVCO LYCOMING ENGINES AIRCRAFT INSTALLATIONS TIO-540-J2BD Piper PA-31-350; LTIO-540-J2BD STC SA1151SO and SA970SO Colemill conversion of Piper PA-31, PA-31-325 and PA-31-350; STC SA980NW Machen Industries conversion of Piper Aerostar 600 STC SA762NW Machen Industries conversion of Beechcraft Bonanza B35 and A36 series.To detect loose distributor gear rotating electrodes on magnetos having 100 hours or more in service since new or overhaul, accomplish paragraph c, before further flight, unless previously accomplished, and every 50 hours in service thereafter until the gears are replaced with laser welded gear assemblies identified by the presence of the letter "Z" or the letters "XO" on the retaining ring end of the gear axle. b. All D-3000 and D-3200 series (blue) magnetos with serial numbers 100 through 1968 not covered by paragraph a, unless previously accomplished. To detect loose distributor gear rotating electrodes on magnetos having 100 hours or more in service since new or overhaul, accomplish paragraph c, before the expiration of 50 hours in service since new or overhaul after the effective date of this AD unless previously accomplished and every 50 hours in service thereafter until the gears are replaced with laser welded gear assemblies identified by the presence of the letter"Z" or the letters "XO" on the retaining ring end of the gear axle or the letter "L", stamped on the distributor gear electrode. c. 1. Remove the distributor block from the magneto and the gears from the block. 2. (A). Inspect distributor gears and block for the presence of bronze colored particles and for indications of metal to metal contact of electrodes. (B). Inspect rotating electrode for looseness by holding the gear in one hand while attempting to move the distributor gear electrode relative to the axle, clock-wise and vertically. Any looseness of the rotating electrode is reason for rejection of distributor gear. 3. If the distributor block is contaminated with brass filings or bronze colored dust, inspect the engine as follows: (A). Observe engine pistons through spark plug hole for evidence of burning. (B). Check valve dry tappet clearance per engine manufacturer's instructions. If piston damage or lower than specified dry tappet clearance is present, the engine must be inspected, in accordance with the engine manufacturer's instructions, for continued airworthiness. 4. Reinstall serviceable distributor gears into a clean serviceable distributor block. Reassemble the magneto and check timing as appropriate. 5. (A). Make an engine log entry of compliance, including magneto serial number. (B). When the laser beam welded distributor gear has been installed in a D-3000 or D-3200 series magneto, identify that magneto by metal stamping the letter "X", on the upper left area of magneto data plate and make the appropriate log entry. Equivalent inspections and procedures must be approved by the Chief of the Engineering and Manufacturing Branch, AEA-210, Federal Aviation Administration (FAA) Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this AD can be accomplished. (Bendix Service Bulletins 618 and 619 pertain to paragraphs a and b respectively.) This Airworthiness Directive is effective November 12, 1981, and paragraph a. was effective upon receipt for all recipients of airmail letter dated June 5, 1981, which covered that subject.
2021-04-08: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B3 helicopters. This AD requires modifying the electrical system of the throttle twist grip, inspecting the routing of a microswitch electrical harness, and correcting the electrical harness routing if it is incorrect. This AD was prompted by reports of the engine remaining in idle when the twist grip was turned from the ''forced idle'' position to the ''flight'' position. The actions of this AD are intended to address an unsafe condition on these products.
2010-14-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It has been evidenced by test that the tightening torque settings on the Rolls-Royce Trent 500 and Trent 700 forward (FWD) and aft (AFT) engine mount link pin retention bolts have always been higher than the design value. These bolts retain the washers that maintain the engine mount vertical load pins in position. If bolts, as a consequence of the over-torque, fail and move away, it would lead to loss of the vertical load pins, which could result in loss of the primary and/or secondary load path of the forward and/or aft engine mount which could potentially lead to engine separation. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
99-03-02: This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model MD-11 series airplanes. This action requires a one-time inspection to detect discrepancies of certain wiring and insulation in the cockpit and cabin, and repair, if necessary. This amendment is prompted by test results obtained in support of an accident investigation. The actions specified in this AD are intended to prevent electrical arcing of certain wiring, which could cause a fire and/or smoke in the cockpit or cabin.
97-19-07: 97-19-07 DASSAULT AVIATION: Amendment 39-10127. Docket 97-NM-182-AD. Applicability: All Model Falcon 2000 series airplanes, certificated in any category. NOTE 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 (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. Compliance: Required as indicated, unless accomplished previously. To prevent an engineflame-out during a rapid throttle reduction, accomplish the following: (a) Within 7 days after the effective date of this AD, revise the Limitations and Abnormal Procedures Sections of the FAA-approved Airplane Flight Manual (AFM), in accordance with Dassault Service Bulletin F2000-80 (F2000-283), dated December 11, 1996. NOTE 2: This may be accomplished by inserting a copy of Temporary Change No. 34 (undated) to the Falcon 2000 AFM into the AFM. When this temporary revision has been incorporated in the general revisions of the AFM, the general revisions may be inserted in the AFM, provided the information contained in the general revisions is identical to that specified in Temporary Change No. 34. (b) Within 30 days after the effective date of this AD, install new placards stipulating the types of airplane fuel to be used, in accordance with Dassault Aviation Service Bulletin F2000-80 (F2000- 28-3), dated December 11, 1996. (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 3: 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 actions shall be done in accordance with Dassault Service Bulletin F2000-80 (F2000- 28-3), dated December 11, 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 Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, New Jersey. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 4: The subject of this AD is addressed in French airworthiness directive 96-290-001(B), dated December 4, 1996. (f) This amendment becomes effective on September 29, 1997.
2022-11-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, EC130B4, and EC130T2 helicopters. This AD was prompted by the identification of certain parts needing maintenance actions, including life limits and maintenance tasks. This AD requires incorporating into maintenance records requirements (airworthiness limitations), as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-14-09: We are superseding airworthiness directive (AD) 2012-14-04 for certain Bombardier, Inc. Model DHC-8-100, -200, and -300 series airplanes. AD 2012-14-04 required replacing certain parking brake accumulators. This new AD retains this requirement. This new AD also requires installing restraint devices around the parking brake accumulator end caps. We are issuing this AD to prevent failure of a parking brake accumulator screw cap or end cap resulting in loss of the number 2 hydraulic system and damage to airplane structures, which could adversely affect the controllability of the airplane.
99-02-13: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters, that requires the replacement of certain main rotor hub spindles (spindles) and flapping hinge pins (pins). This amendment is prompted by testing of aged frequency adapters, which shows that premature failure of the spindles and pins can occur due to increased loading from increased stiffness of the aged frequency adapters. The actions specified by this AD are intended to prevent the loss of a main rotor blade and subsequent loss of control of the helicopter.
89-12-06: 89-12-06 BRITISH AEROSPACE: Amendment 39-6226. Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent structural failure of the fuselage accomplish the following: A. Prior to the accumulation of 30,000 landings or within 1,600 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,600 landings, perform visual inspections of the fuselage frame splice joint, skin, stringers, and connecting structure at fuselage station 178 between stringers 2 left and 2 right in accordance with British Aerospace Alert Service Bulletin 53-A-PM5964, Issue 2, dated June 1, 1988. Any cracks found must be repaired prior to further flight, in accordance with the service bulletin. B. If cracks are found during inspections required by paragraph A., perform additional inspections in accordance with paragraph 2.2. of the Accomplishment Instructions, of British Aerospace Alert Service Bulletin 53-A-PM5964, Issue 2, dated June 1, 1988, and repair all cracks, prior to further flight, in accordance with the service bulletin. C. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. 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 requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Inc., Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6226, AD 89-12-06) becomes effective on July 3, 1989.
93-08-09: 93-08-09 FAIRCHILD AIRCRAFT: Amendment 39-8556. Docket No. 93-CE-28-AD. Applicability: Models SA227-TT, SA227-AT, SA227-AC, and SA227-BC, airplanes (all serial numbers), certificated in any category that have the nose wheel steering system modified in accordance with Fairchild Service Bulletin (SB) 227-32-030, Issued: February 22, 1991, Revised: October 5, 1991; and Model SA227-DC airplanes (serial numbers 784 and 790 through 825), certificated in any category. Compliance: Required within the next 25 hours time-in-service, unless already accomplished. To prevent loss of directional control of the airplane during takeoff or landing caused by nose wheel steering malfunctions, accomplish the following: (a) For the Models SA227-TT, SA227-AT, SA227-AC, and SA227-BC airplanes, place a copy of this AD into the Limitations Section of the Airplane Flight Manual (AFM) in order to incorporate the following nose wheel steering system limitations: (1) Check the nose wheel steering prior to each takeoff using the procedures in the Normal Procedures section of the airplane flight manual. (2) The use of nose wheel steering for takeoff and landing is prohibited. Prior to each takeoff, turn the nose wheel arm switch to "OFF", and do not turn to "ON" until after landing and the airplane has slowed to taxi speed. (b) For the Model SA227-DC airplanes, incorporate FAA-Approved Model SA227-DC AFM Revision 8, dated April 2, 1993, into the Limitations Section of the AFM. This AFM revision specifies nose wheel steering limitations. (c) 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. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Aircraft 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. (e) All persons affected by this directive may obtain a copy of the document referenced from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine information related to this AD at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (f) This amendment becomes effective on May 14, 1993.
62-16-02: 62-16-02 DOUGLAS: Amdt. 462 Part 507 Federal Register July 12, 1962. Applies to All Model DC-8 Aircraft With Outboard Flap Actuating Cylinder Douglas P/N 3643686. These Cylinders Can Be Identified As Having An Outside Diameter of 3.810-3.820 Inches At The Forward End Of The Barrel Where The Cylinders Attach To The Wing Flap Crank. \n\n\tCompliance required as indicated. \n\n\t(a) On aircraft incorporating flap quadrant stops which limit flap extension to 40 degrees full down, conduct a close visual inspection daily of the forward 1/4 inch of length and around the entire periphery of both outboard wing flap actuating cylinder barrels for evidence of cracks or fluid leakage. Conduct inspection with hydraulic pressure on. Investigate hydraulic fluid leakage to determine cause. Barrels showing evidence of cracks shall be replaced prior to further flight. \n\n\t(b) On aircraft not incorporating 40 degrees full-down quadrant stops, prior to each flight inspect in accordance with (a) until aircraft are modified as follows: \n\n\t\t(1) Install a stop on the control pedestal assembly as described on Serial E.0.001 to Douglas Drawing 5640901 which restricts flap extension to 46-48 degrees down travel or, install a new flap position quadrant, flap-detent locating nameplate and flap position placard in accordance with Figure (2) of Douglas DC-8 Service Bulletin No. 27-134 or FAA approved equivalent. \n\n\t\t(2) Rig the flap in accordance with the instructions contained in Addendum No. 1 dated June 12, 1962, to Douglas Alert Bulletin A27-134 or rig the flap in accordance with (d)(3). \n\n\t(c) When modifications in accordance with (b) have been accomplished, the preflight inspection required by (b) may be conducted daily. \n\n\t(d) The daily or preflight inspections required in (a), (b) and (c) may be discontinued if the following is accomplished: \n\n\t\t(1) Conduct initial inspection of both outboard barrel assemblies, P/N 3643686-1, in accordance with steps (1) through (4)of Figure (1) in DC-8 Service Bulletin No. 27-134. Barrels meeting the inspection requirements specified therein, may be continued in service. After this initial inspection, periodically reinspect barrels for cracks in accordance with step (1), mentioned above, at intervals not to exceed 2,500 hours' time in service thereafter. Barrels showing evidence of cracks shall be replaced prior to further flight. \n\n\t\t(2) Accomplish rework outlined in paragraph (b) (1). \n\n\t\t(3) Adjust all flap actuating cylinders and rig the flaps to the pertinent dimensions, flap travel limits and flap travel times specified in paragraph 2, Accomplishment Instructions, Kit C or D, paragraph E of Douglas DC-8 Service Bulletin No. 27-134, or an FAA approved equivalent. \n\n\t(e) The magnetic inspection, step (1), specified in (d)(1), may be discontinued: \n\n\t\t(1) After the fourth such inspection if the barrels, P/N 3643686-1, meet the inspection requirements of (d)(1), are shot peened in accordance with Figure (1) of Douglas DC-8 Service Bulletin No. 27-134, reidentified as P/N 3643686-501, and further identified with a color code or FAA approved equivalent; or \n\n\t\t(2) Upon installation of new shot peened barrels, P/N's 3643686-501 or 3774061-501. \n\n\t(f) Upon request of the operator an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western 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(Douglas DC-8 Service Bulletin No. 27-134 dated July 20, 1962, covers this 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 telegrams dated June 7, 1962, and June 14, 1962. \n\n\tRevised November 3, 1962.
2022-09-08: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports of a missing shim at a joint common to the main torque box (MTB) skin panel and rear spar root fitting. This AD requires inspecting the MTB skin panel and rear spar root fitting for cracking and delamination, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2010-13-12: We are adopting a new airworthiness directive (AD) for certain Model 747 series airplanes. This AD requires replacing the power control relays for the main tank fuel boost pumps and jettison pumps, and the center tank scavenge pump, as applicable, with new relays having a ground fault interrupt (GFI) feature. This AD also requires revising the maintenance program to incorporate Airworthiness Limitations (AWLs) 28-AWL-23 (for Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SP, and 747SR series airplanes), and AWLs 28-AWL-28 and 28-AWL-29 (for Model 747-400, 747- 400D, and 747-400F series airplanes). This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent damage to the fuel pumps caused by electrical arcing that could introduce an ignition source in the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
98-26-06: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-26-06 which was sent previously to all known U.S. owners and operators of Schweizer Aircraft Corporation (Schweizer) Model 269D helicopters by individual letters. This AD requires removing the main rotor drive shaft (shaft) and inspecting it for cracks. If a crack is found, replacing the shaft with an airworthy shaft is required. This AD also requires periodically verifying the torque of the main rotor hub (hub) bolts. This amendment is prompted by four reports of cracking in the shaft of helicopters with a large diameter hub. Wear patterns indicate cracking was caused by loss of clamping torque on the hub and shaft assembly due to the use of grease between the hub and shaft. This condition, if not corrected, could result in failure of the shaft and subsequent loss of control of the helicopter.
2022-11-19: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. Model 212, 412, 412CF, and 412EP helicopters. This AD was prompted by a report of a cracked check valve. This AD requires inspecting certain engine oil and fuel check valves, and depending on the results, repetitively inspecting and removing the check valve from service. This AD also prohibits installing affected engine oil and fuel check valves on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
81-17-01: 81-17-01 BENDIX: Amendment 39-4183. Applies to Bendix Starting Vibrator Assemblies, Part Numbers 10-176485-121, -122, -241, -242; 10-382780-12, -24 installed in but not limited to the following aircraft powered by reciprocating engines. Bell (Textron) Model 47 series helicopters Brantley (Hynes) Model B2 series helicopters Enstrom Model F28, F28A, F28F; 280, 280F helicopters, Model F28C and 280C helicopters equipped with Avco Lycoming HIO-360-E1BD engines Hughes (Summa Corp.) Model 269 series helicopters Hiller (Fairchild Industries) Model UH12 series helicopters Robinson Model R-22 series helicopters To preclude the loss of ignition due to the grounding of both "P" (Primary) leads within the starting vibrator, accomplish the alteration and identification shown in the Detailed Instruction of Bendix Engine Products Division Service Bulletin No. 614 or an FAA approved equivalent within the next 25 hours time in service after the effective date of this ADunless previously accomplished. Equivalent inspections and Procedures must be approved by the Chief of the Engineering and Manufacturing Branch, AEA-210, Federal Aviation Administration (FAA) Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this airworthiness directive can be accomplished. This amendment becomes effective August 13, 1981.
2021-03-01: The FAA is superseding Airworthiness Directive (AD) 2018-05- 09, which applied to all Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. AD 2018-05-09 required inspecting the tail rotor (T/R) flapping hinge link (hinge) and reporting the results. This AD requires repetitive inspections of the spindle bolts and the inner ring and needle bearings of each flapping hinge, corrective actions if necessary, and repetitive replacements of affected flapping hinge components, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. Replacement of all affected flapping hinge components on each flapping hinge is terminating action for the repetitive inspections. This AD also expands the applicability. This AD was prompted by a report of a damaged flapping hinge on a T/R blade. The FAA is issuing this AD to address the unsafe condition on these products.
99-02-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes, that requires modification of the power supply system of the horizontal stabilizer control unit. 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 loss of primary hydraulic stabilizer control during use of certain emergency procedures, which could result in the inability of the flight crew to control the airplane.
88-09-02: 88-09-02 CASA: Amendment 39-5899. Applies to Model C-212 series airplanes, serial numbers as listed in CASA Service Bulletin 212-28-15, dated April 11, 1983, certificated in any category. Compliance is required within 5 months after the effective date of this AD, unless previously accomplished. To prevent inability to close fuel shut-off valves in the event of a fire, accomplish the following: A. Replace the fuel shut-off valves with new modified valves, in accordance with CASA C-212 Service Bulletin 212-28-15, dated April 11, 1983. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, 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 accomplishmentof the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Contrucciones Aeronauticas S.A., Getafe, Madrid, Spain. 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 39-5899 becomes effective June 1, 1988.
2022-10-09: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA-365C1 and SA-365C2 helicopters. This AD was prompted by a Model EC225 helicopter accident and subsequent investigation that determined that the level of particles in certain main gearboxes (MGB) could lead to a planet gear seizure. This AD requires inspecting the MGB magnetic plugs and oil filter for particles and, depending on the outcome of the inspections, further inspections and replacing certain parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
93-13-03: 93-13-03 BRITISH AEROSPACE (COMMERCIAL AIRCRAFT), LIMITED: Amendment 39-8616. Docket 93-NM-89-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2055, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent operational failure of the fire extinguisher systems for the left- and right-hand engines, accomplish the following: (a) Within 14 days after the effective date of this AD, perform a safety ohmmeter inspection to verify the electrical conductivity of the firing circuits at the cartridge connectors of the fire extinguisher bottles of the left- and right-hand engines in accordance with Jetstream Aircraft, Ltd., Service Bulletin ATP-26-9, dated May 12, 1993. (1) If an out-of-tolerance condition is not detected: No further action is required by this paragraph. NOTE: An "out-of-tolerance condition" is defined as having an electrical resistance reading of less than 5.5 ohms or greater than 7 ohms. (2) If an out-of-tolerance condition is detected: Prior to further flight, perform a full electrical inspection of the fire extinguisher systems of the left- and right-hand engines and repeat the safety ohmmeter inspection in accordance with the service bulletin. (i) If an out-of-tolerance condition is no longer detected: No further action is required by this paragraph. (ii) If an out-of-tolerance condition is still detected: Prior to further flight, replace the cartridge firing unit with a new or serviceable cartridge firing unit and/or replace the cartridge connector with a new or serviceable cartridge connector in accordance with the service bulletin. (b) Within 10 days after accomplishing the inspection(s) required by paragraph (a) of this AD, submit a report of any inspection findings, to Jetstream Aircraft, Ltd., in accordance with Jetstream Aircraft, Ltd., Service Bulletin ATP-26-9, dated May 12, 1993. Report all findings, including nil defects, to: Service Support Manager, Customer Support Department, Jetstream Aircraft, Ltd., Woodford Aerodrome, Chester Road, Cheshire SK7 1QR, England. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (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: 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 FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspections and replacement shall be done in accordance with Jetstream Aircraft, Ltd., Service Bulletin ATP-26-9, dated May 12, 1993. 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 Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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 July 19, 1993.
99-02-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that requires modification of the aft cabin sidewall area to improve decompression venting and, for certain airplanes, modification of the aft wardrobe/stowage area door and installation of decompression panels to improve decompression venting. 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 damage to the cabin floor in the event of sudden decompression in the cargo compartment, which could result in injury to passengers, reduced structural integrity of the airplane, and the loss of airplane systems.
85-19-51 R1: 85-19-51 R1 PRATT & WHITNEY AIRCRAFT: Amendment 39-5168. Applies to Pratt and Whitney Aircraft JT8D-15, -17, and -17R turbofan engines. Compliance is required as indicated unless already accomplished. To prevent possible failure of the second stage turbine disk, inspect second stage turbine disk, Part Numbers 676802, 770602, 780502, 786802, and 787302 details, and Part Numbers 676822, 769722, 769832, 786822, and 787232 assemblies for wear and cracking of the snap diameter and at the bottom of the disk airseal groove, repair the disk, and modify the mating third stage turbine inner airseal in accordance with the Accomplishment Instructions (Paragraph 2) of PWA Alert SB 5541, Revision 1, dated May 4, 1984, and PWA SB 5510, Revision 1, dated February 13, 1984, or FAA approved equivalents, per the following schedule: (a) For disks which have not had the airseal groove previously repaired: (1) With 14,000 hours or more time in service since new - inspect, repair andmodify prior to reaching 17,000 hours time in service since new or within the next 2,000 hours time in service, whichever occurs first. (2) With less than 14,000 hours time in service since new - inspect, repair and modify by 14,000 hours time in service since new or within the next 2,000 hours time in service, whichever occurs later. (b) For disks which have had the airseal groove previously repaired: (1) With 2,000 hours or more time in service since repair - inspect, repair, and modify within the next 400 hours time in service. (2) With less than 2,000 hours time in service since repair, inspect, repair and modify by 2,000 hours time in service since repair or within the next 400 hours time in service, whichever occurs later. Disks worn beyond the repair limits of the applicable SB's must be removed from service. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an owner or operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance schedule specified in this AD. PWA SB Number 5510, Revision 1, dated February 13, 1984, and the Accomplishment Instructions of (Paragraph 2) PWA Alert SB 5541, Revision 1, dated May 4, 1984, 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 Pratt & Whitney Aircraft Group, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108.These documents also may be examined at the Office of Regional Counsel, New England Region, FAA, Room No. 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday though Friday except Federal holidays. This amendment supersedes Amendment 39-4879 (49 FR 37568) AD 84-16-03. Those provisions of this amendment which apply to unrepaired disks become effective on December 26, 1985. The remaining provisions of this amendment become effective December 26, 1985, except to those persons to whom they were made immediately effective by individual telegrams issued September 25, 1985.
68-23-06: 68-23-06 BEECH: Amendment 39-684. Applies to Models D18C, D18S, E18S, E18S- 9700, G18S, H18, C45G, TC45G, C45H, TC45H, TC-45J (SNB-5), and JRB-6 with Volpar Tri- Gears, Serial Numbers 1 through 368, installed in accordance with STC SA111-WE or SA4- 1531. Compliance is required within the next six calendar months after the effective date of this AD, unless already accomplished. Repetition thereafter is not necessary. To determine the possible presence of corrosion and to provide a moisture barrier for the internal portion of the Beech center section wing truss assembly, accomplish the following: (a) Remove two bolts at each attachment point where the Volpar truss in each nacelle is secured to the center section wing truss as shown in Figure Nos. 1 and 2 of Volpar Service Bulletin no. 14. Dry and seal tubes from which bolts were removed in accordance with paragraphs 1 and 2 of Volpar Service Bulletin No. 14 or later FAA approved revision. (b) Remove the bolt which passes through the lower sparcap just inboard of each outer wing attach point as shown in Figure 3 of Volpar Service Bulletin No. 14. Inspect the bolts for corrosion and pitting, and the edges of the bolt hole through the elliptical spar tube for indications of moisture and/or corrosion. If pitting of the bolts exceeds .005 inches in depth or if evidence of moisture or corrosion exists, further inspections outlined under (c), below, must be accomplished. Otherwise dry and seal the lower spar cap in accordance with paragraphs 1 and 2 of Volpar Service Bulletin No. 14, or later FAA approved revision. (c) Conduct an x-ray inspection of the elliptical lower spar cap outboard of the wing to fuselage intersection for evidence of internal corrosion in accordance with Volpar Service Bulletin No. 14 and Report No. 34 or latter FAA approved revisions. If corrosion is indicated by this inspection, before further flight, the part must be replaced or the extent of corrosion and the corrective action to be taken must be evaluated by Volpar, Inc., and concurred in by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Upon satisfactory completion of (c), dry and seal the lower spar cap as specified in (b), above. (e) Modify the Volpar Part No. 299-2 drag strut by cutting off the lug for the bolt in accordance with Figure 3 of Volpar Service Bulletin No. 14. Install Volpar Part No. 873 strap installation and Volpar Part No. 873-2 strap or an equivalent approved by the Chief Aircraft Engineering Division, FAA Western Region. (f) Aircraft with corrosion found pursuant to (c) of this AD may be flown in accordance with FAR 21.197 to a base where further evaluation or repair may be accomplished. This amendment becomes effective December 19, 1968.
2013-15-20: We are superseding emergency airworthiness directive (AD) 2013-14-51 for General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines with affected transfer gearbox assembly (TGB) radial gearshafts installed. AD 2013-14-51 was sent previously to all known U.S. owners and operators of GE90-110B1 and GE90-115B turbofan engines. AD 2013-14-51 prohibited operation of an airplane if more than one installed engine has an affected TGB radial [[Page 47535]] gearshaft. This AD contains the same prohibition as AD 2013-14-51 and also prohibits operation of any airplane 60 days after the effective date of this new AD if any installed engine has an affected TGB radial gearshaft. This new AD also revises the applicability by adding GE90- 76B, GE90-77B, GE90-85B, GE90-90B, GE90-94B, and GE90-113B turbofan engine models and adds a mandatory terminating action. This new AD was prompted by reports of three failures of TGB radial gearshafts which resulted in in-flight shutdowns (IFSDs). We are issuing this new AD to prevent failure of the TGB radial gearshaft, which could result in IFSD of one or more engines, loss of thrust control, and damage to the airplane.