Results
87-21-09: 87-21-09 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 5747. Applies to all Model AS 332C and L helicopters certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent loss of the AC electrical generation system, accomplish the following: (a) Within the next 50 hours' time in service or the next 30 days after the effective date of this AD, inspect the electrical cable bundles connecting each AC generator to its regulating card in accordance with the instructions given in paragraph BBA of Aerospatiale Telex Service No. 05.12, transmitted by Aerospatiale Telex No. 10084, dated January 16, 1987. (b) The aircraft can be returned to operational service if the insulation values measured are greater than 2 megohms. (c) If the insulation values measured are less than 2 megohms, the installation is to be modified in accordance with the instructions given in Aerospatiale AS 332 Service Bulletin No. 24.10,paragraph 2, "Accomplishment Instructions." (d) Within 400 hours' time in service following the inspection or before December 31, 1987, whichever occurs first, modify the aircraft in accordance with the instructions given in AS 332 Service Bulletin No. 24.10, paragraph 2, "Accomplishment Instructions." (e) An alternate means of compliance which provides an equivalent level of safety may be used if approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, Fort Worth, Texas 76193-0100. This amendment becomes effective November 12, 1987.
2018-16-08: We are adopting a new airworthiness directive (AD) for Leonardo S.p.A. (Leonardo) Model A109E, A109S, and AW109SP helicopters with an oil cooler fan assembly (fan assembly) installed. This AD requires inspecting each oil cooler system pulley assembly (pulley assembly) bearing and replacing each fan assembly. This AD is prompted by reports of degraded pulley assembly bearings. The actions of this AD are intended to correct an unsafe condition on these products.
65-28-03: 65-28-03 MACCHI: Amdt. 39-167 Part 39 Federal Register December 14, 1965. Applies to Models AL 60 and AL 60-B Airplanes. Compliance required as indicated. To prevent further failures of the threaded shank of the eyebolt, Heim Company P/N M44-14, located at the elevator center hinge, accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD, visually, or by use of other FAA-approved methods, inspect the threaded shank of the eyebolt, Heim Company P/N M44-14. (b) If no cracks are found, repeat the inspection specified in (a) at intervals not to exceed 25 hours' time in service from the previous inspection. (c) If cracks are found, replace the eyebolt. If the replacement eyebolt is of the same part number, the repetitive inspections required by (b) must be continued. (d) The repetitive inspection required by (b) may be discontinued when Aermacchi Modification No. AL60/24, installation of eyebolt Heim Company P/N MD46-15, or an FAA- approved equivalent is accomplished. (Aeronautical Macchi Service Bulletin No. AL60/11 and Modification Bulletin No. AL60/24 covers this subject.) This directive effective January 13, 1966.
48-02-06: 48-02-06 DOUGLAS: Applies to DC-6 Serial Numbers 42854 Through 42896; 43000 Through 43018; 43025; 43055 Through 43057; 43062 Through 43064; and 43105. \n\n\tCompliance required by March 1, 1948. \n\n\tAs a fire protection measure, close off the dead air space between the upper and lower wing surfaces within the engine nacelle by installing cover plates over the open access hole in the lower surface of the wing in the right and left inboard nacelles between center and front spars and between Stations 130 and 167. \n\n\t(Douglas Service Bulletin DC-6 No. 92 covers this same subject.)
65-24-01: 65-24-01 AIR CRUISERS: Amdt. 39-149, Part 39 Federal Register October 13, 1965. Applies to Emergency Evacuation Slides, P/N 15D22129, Installed on Boeing Model 727 Series Airplanes. \n\n\tCompliance required within the next 1,000 hours' time in service after the effective date of this AD unless already accomplished. \n\n\tTo prevent ripping of Air Cruisers emergency evacuation slides, P/N 15D22129, rework and reinforce each slide in accordance with the Accomplishment Instructions specified in Air Cruisers Service Bulletin SB-114-65-1, Revision A, dated March 19, 1965, or later FAA-approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. \n\n\tThis directive effective November 12, 1965.
65-21-03: 65-21-03 DOUGLAS: Amdt. 39-133 Part 39 Federal Register September 4, 1965. Applies to Model DC-8 Airplanes. \n\n\tCompliance required as indicated. \n\n\tTo prevent further failures of the main landing gear strut piston due to cracking in the radius of the torque link lug, accomplish the following on landing gear strut piston assemblies, Douglas P/N's 5598229, 5598343, 5719155, 5773028, 5773029, and 5773030: \n\n\t(a)\tUnless already accomplished, rework assemblies having 4,000 or more hours' time in service on the effective date of this AD - \n\n\t\t(1)\tIn accordance with paragraph 2B of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 4,500 hours' time in service after the effective date of this AD; or \n\n\t\t(2)\tIn accordance with Douglas TWX MISC-108/DJW dated January 28, 1963, within 500 hours' time in service after the effective date of this AD and in accordance with paragraph 2A of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 4,500 hours' time in service after the effective date of this AD. \n\n\t(b)\tUnless already accomplished, rework assemblies having less than 4,000 hours' time in service on the effective date of this AD - \n\n\t\t(1)\tIn accordance with paragraph 2B of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before the accumulation of 8,500 hours' time in service; or \n\n\t\t(2)\tIn accordance with Douglas TWX MIS-108/DJW dated January 28, 1963, before the accumulation of 4,500 hours' time in service and in accordance with paragraph 2A of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before the accumulation of 8,500 hours' time in service. \n\n\t(c)\tInspect assemblies with 4,000 or more hours' time in service on the effective date of this AD that have not been reworked in accordance with Douglas TWX MISC-108/DJW dated January 28, 1963, in the area of the radius between the main landing gear strut piston torque link lugs for cracks using a dye penetrant inspection method or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 500 hours' time in service after the effective date of this AD unless already accomplished within the last 500 hours' time in service and thereafter at intervals not to exceed 1,000 hours' time in service from the last inspection. \n\n\t(d)\tInspect assemblies with less than 4,000 hours' time in service on the effective date of this AD that have not been reworked in accordance with Douglas TWX MISC-108/DJW in the area of the radius between the main landing gear strut piston torque link lugs for cracks using a dye penetrant inspection method or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before the accumulation of 4,500 hours' time in service unless already accomplished within the last 500 hours' time in service and thereafter at intervals not to exceed 1,000 hours' time in service from the last inspection. \n\n\t(e)\tReplace any part having a crack 0.040 inch or more in depth with an undamaged part before further flight. Replace any part having a crack less than 0.040 inch in depth with an undamaged part before further flight or rework it in accordance with paragraph 2B of Douglas Service Bulletin No. 32-99, Revision No. 3, dated October 30, 1964, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, before further flight. \n\n\t(f)\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust therepetitive 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\tThis directive effective October 4, 1965.
2018-15-07: We are adopting a new airworthiness directive (AD) for certain Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 an incorrect part number for the rudder trim actuator is referenced in the Airworthiness Limitations section of the FAA-approved maintenance program (e.g., maintenance manual) and the life limit for that part may not be properly applied in service. We are issuing this AD to require actions to address the unsafe condition on these products.
85-03-04 R2: 85-03-04 R2 GULFSTREAM AEROSPACE (ROCKWELL): Amendment 39-5003 as amended by Amendment 39-5587. Applies to Models 112 (S/N' s 1 through 499); 112TC (S/N's 13000 through 13149); and 114 (S/N's 14000 through 14149) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To improve seat retention and passenger restraint during crash landing or accident impact, accomplish the following: (a) Within the next 100 hours time-in-service, or one calendar year after the effective date of this AD, whichever comes first, modify the front seats and belt attachments in accordance with one of the following modifications: (1) Rockwell Service Bulletin Nos. SB-112-45A or SB-114-5A, both dated April 7, 1977, as applicable, or (2) Gulfstream Aerospace Service Bulletin Nos. SB-1l2-70A, Revision 1, or SB-114-21A, Revision 1, both dated February 23, 1987, as applicable. NOTE: The modification specified in paragraph (a) (1) above is the modification referenced in AD 77-16-09. The modification specified in paragraph (a) (2) above is the modification referenced in AD 85-03-04 R1. (b) The airplane may be flown in accordance with FAR 21.197 to a location where the repair can be performed. (c) An equivalent method of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas 76101; Telephone (817) 624-5150. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Gulfstream Aerospace Corporation, Wiley Post Airport, P.O. Box 22500, Oklahoma City, Oklahoma 73123; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5003 superseded AD 77-16-09 which was effective March 25, 1985. Effective date of Amendment 39-5003 was suspended July 2, 1985. This amendment, 39-5587, becomes effective April 27, 1987.
70-10-02: 70-10-02 PRATT & WHITNEY: Amdt. 39-984. Applies to all Pratt & Whitney Aircraft R-985 and Wasp Jr. type engines altered in accordance with Supplemental Type Certificate No. SE1-391 incorporating Simmonds Precision Part No. 580047, fuel injector. Compliance required as indicated. To prevent engine power loss as the result of failure of the gerotor pump drive pin or the plugging of the fuel injector filter, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD and thereafter at intervals of 100 hours time in service inspect and clean the fuel injector filter P/N 580436. (b) Overhaul the fuel injector P/N 580047 prior to the accumulation of 600 hours time in service. For injectors with more than 550 hours time in service on the effective date of this AD overhaul the injector within the next 50 hours time in service. (c) Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineeringand Manufacturing Branch, FAA Eastern Region may adjust the repetitive inspection intervals specified in this AD. This amendment is effective June 9, 1970.
2018-15-08: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 airplane sound insulation materials attached to the aft face of the firewall not complying with the applicable burn testing criteria for materials on the cabin side of the firewall. We are issuing this AD to require actions to address the unsafe condition on these products.
2018-15-01: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) Trent 1000-A, Trent 1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, Trent 1000-H, Trent 1000-A2, Trent 1000-C2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 engine models. This AD requires certain engines susceptible to intermediate-pressure turbine (IPT) blade failure not be installed on an airplane together with other engines with IPT blades of the same age. This AD was prompted by new operating restrictions for engines with IPT blades susceptible to shank corrosion and possible blade separation. We are issuing this AD to address the unsafe condition on these products.
48-33-01: 48-33-01 LOCKHEED: Applies to All 49-46, 149-46, 649-79 and 749-79 Models, Through Serial Number 2588. Compliance with new placard restrictions required immediately. Placards to be installed not later than December 1, 1948. Remove existing fuel placards and install three new placards covering fuel system operational procedure. A. The placard to be removed from the 49-46 airplane is located on the Flight Engineer's lower instrument panel and reads: "CAUTION: Do Not Land With More Than 900 Gallons of Fuel in Each Outer Tank". B. The placard to be removed from the 649 airplane is located on the Flight Engineer's uppermost panel and reads: "Fuel Load Restrictions Model 749. Takeoff: Do not Takeoff with Less Than the Following Fuel Loads": The placards to be added read as follows: 1. "This Airplane Must be Fueled, and Fuel Used, in Accordance With the Charts in the Approved Operating Manual." (LAC, Part M302166). 2. "At All Times, Fuel in Tanks 2 and 3 Must Not Exceed Fuel in Tanks 1 and 4, Respectively." (LAC, Part M302163.) 3. "Fuel Transfer from one Tank to Another is not Permitted. When Operating the Fuel System on Crossfeed, the Tanks not Being Used Must be Turned Off." (LAC, Part M302109.) (On Models 49-46, 149, 649, and 749 install placard 1 on Pilot's instrument panel and placards 1, 2, and 3, on Flight Engineer's uppermost instrument panel. Placard 3 has been installed on airplane Serial Number 2577 and subsequent, prior to delivery. (LAC Service Bulletin 49/SB-439, dated March 23, 1948 covers this same subject.)
2005-01-15 R1: The FAA is revising an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 875, 877, 884, 884B, 892, 892B, and 895 series turbofan engines with certain part number (P/N) low pressure compressor (LPC) fan blades installed. That AD currently requires initial and repetitive ultrasonic inspections of the fan blade dovetail roots and defines a specific terminating action to the repetitive blade inspection requirements. This AD requires the same actions but clarifies the terminating action. We are issuing this AD to prevent multiple LPC fan blade failures due to cracks, which could result in uncontained engine failure and possible damage to the airplane. DATES: This AD becomes effective October 17, 2005. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of January 28, 2005 (70 FR 2336, January 13, 2005).
2018-15-05: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-115, -132, and -133 airplanes; and Model A320- 214, -216, -232, -233, -251N, and -271N airplanes. This AD was prompted by reports of safety pins that had been installed on the inflation reservoirs of escape slides/slide rafts during production, but had not been removed. This AD requires inspecting each passenger escape slide/ slide raft to determine whether the safety pin is installed on the slide inflation reservoir, and removing any installed safety pin. We are issuing this AD to address the unsafe condition on these products.
2018-14-09: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of early cracking on certain holes of the crossbeam splicing at certain fuselage frames. This AD requires repetitive inspections for cracking of the fastener holes in certain fuselage frames, and depending on airplane configuration, provides an optional terminating action to the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
89-15-08: 89-15-08 BOEING: Amendment 39-6269. \n\tApplicability: All Model 737 series airplanes through line number 1581, equipped with a second observer's seat, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo ensure structural integrity of the second observer's seat, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, install a placard above the second observer's seat, stating: "NO OCCUPANCY." This placard may be removed once the terminating action of paragraph B., below, has been accomplished. \n\n\tB.\tWithin 6 months after the effective date of this AD, inspect the second observer's seat installation for missing fasteners, in accordance with Boeing Service Letter 737-SL-25-41, dated October 14, 1988, or Boeing Service Letter 737-SL-25-41-A, dated April 20, 1989. If fasteners are found to be missing, repair prior to further flight, in accordance with the service letter. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: 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, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Transport Airplane Directorate, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6269, AD 89-15-08) becomes effective on August 24, 1989.
47-10-27: 47-10-27 LOCKHEED: (Was Mandatory Note 30 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2078. Compliance required prior to July 1, 1947. Install new type fuel tank vent outlets and add extension to fuel dump chutes. (LAC Service Bulletin 49/SB-201 covers this same subject.)
65-14-01: 65-14-01 BEECH: Amdt. 39-96 Part 39 Federal Register June 26, 1965. Applies to Models H35, J35, K35, and 35-33 Series Aircraft Equipped with Ellingsworth Products Co., Inc. Alternator Kit Number 195860 Installed Under STC SA1-377. Compliance required within the next 25 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. To prevent further failures of the alternator support bracket, accomplish the following: (a) Remove alternator supporting brackets, P/N's 195814, 195820, 195836, 195838, 195840 and 626131, thoroughly clean and inspect for elongated bolt holes. (b) Inspect brackets not having elongated bolt holes, for cracks using dye penetrant or magnetic particle method or FAA-approved equivalent. (c) Replace brackets having elongated bolt holes or cracks with unused parts of the same part number or FAA-approved equivalent before further flight. (d) Upon request of the operator, and 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. This directive effective June 26, 1965.
2018-12-08: We are superseding Airworthiness Directive (AD) 2017-07-07, which applied to certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. AD 2017-07-07 required repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. This AD retains the requirements of AD 2017-07-07 and expands the applicability. This AD was prompted by a report of cracking at fastener holes located at frame (FR) 40 on the lower shell panel junction. We are issuing this AD to address the unsafe condition on these products.
2018-13-08: We are superseding Airworthiness Directive (AD) 2016-01-11, which applied to certain Airbus Model A320-211, -212, and -231 airplanes. AD 2016-01-11 required repetitive inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame (FR) 36, repetitive inspections for cracking of the fastener holes of the front spar vertical stringers on FR 36, and repair if necessary. This AD adds new thresholds and intervals for the repetitive inspections; requires, for certain airplanes, a potential terminating action modification of the center wing box area; and expands the applicability. This AD was prompted by a report that, during a center fuselage certification full-scale fatigue test, cracks were found on the front spar vertical stringer at a certain frame. This AD was also prompted by a determination that, during further investigations of the frame as part of the widespread fatigue damage (WFD) campaign, certain inspection compliancetimes have to be revised and new inspections and a new potential terminating action modification have to be introduced. We are issuing this AD to address the unsafe condition on these products.
84-23-01: 84-23-01 LOCKHEED: Amendment 39-4955. Applies to Lockheed Models 1329-23A, -23D, - 23E, and -25 series airplanes, serial numbers 5001 through 5162 and 5201 through 5240, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect cracks which could lead to failure of the empennage and loss of the airplane, accomplish the following: A. Within the next 25 hours flying time or within 20 days after the effective date of this airworthiness directive (AD), inspect for cracks, proper hardware, proper installation of hardware, and loose fasteners in the JE24-1 empennage pivot fitting at the point where the fitting attaches to the flange of the JE22-1 rear beam of the vertical stabilizer in accordance with Lockheed Alert Service Bulletins A329II-55-3 and A329-299, dated October 19, 1984. If loose fasteners or cracks are found, before further flight, repair or replace with new or serviceable parts, as necessary, in accordance with a method acceptable to or approved by the FAA. B. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. This amendment becomes effective November 26, 1984.
69-07-01: 69-07-01 BRITISH AIRCRAFT CORPORATION: Amdt. 39-741. Applies to Model BAC 1-11, 200, and 400 Series Airplanes. Compliance required as indicated, unless already accomplished. To prevent interference between the flap rear pick up fitting and the flap link assembly, accomplish the following: (a) For BAC 1-11, 200, and 400 Series Airplanes with flap links P/N AB09A3697 installed, accomplish the following: (1) Within the next 160 hours' time in service after the effective date of this AD, inspect in accordance with paragraph (3) of this section to determine if a minimum clearance of 0.075 inches is provided between the flap rear pick up fitting and the flap link assembly. (2) If the inspection reveals a clearance of less than 0.075 inches, before further flight (except that the airplane may be flown in accordance with Section 21.197 of the Federal Aviation Regulations to a base where the repair can be performed), incorporate BAC Modification PM 2868, as specifiedin paragraph (3) of this section. (3) Perform the inspection and modification required in paragraphs (1) and (2) of this section, in accordance with British Aircraft Corporation BAC 1-11, Alert Service Bulletin No. 27-A-PM 2245, Issue 6, dated September 16, 1968, or later ARB-approved issue, or an FAA approved equivalent. (b) For BAC 1-11, 200, and 400 Series Airplanes with flap links P/N AB09A3657 or P/N AB09A3697 installed, accomplish the following: (1) Within the next 1000 hours' time in service after the effective date of this AD, inspect in accordance with paragraph (3) of this section, the outer link positions at No. 2 and No. 3 flaps, left and right sides, for interference between the flap link and flap rear pick up fitting fork. (2) If the inspection reveals an interference, before further flight (except that the airplane may be flown in accordance with Section 21.197 of the Federal Aviation Regulations to a base where the repair can be performed), incorporate BAC Modification PM 3691, as specified in paragraph (3) of this section. (3) Perform the inspection and modification required in paragraphs (1) and (2) of this section in accordance with British Aircraft Corporation BAC 1-11, Alert Service Bulletin No. 27-A-PM 2245, Issue 6, dated September 16, 1968, or later ARB-approved issue or an FAA-approved equivalent. This amendment effective March 27, 1969.
65-11-01: 65-11-01 BEECH: Amdt. 39-67 Part 39 Federal Register May 20, 1965. Applies to Model 23 Aircraft Serial Numbers M-1 through M-334 except M-62. Compliance required within 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent water from entering the static lines through the fuselage static air ports and causing a system malfunction, accomplish the following or an FAA-approved equivalent: (a) Remove the tee fitting from the static line connection just aft of the rear cabin bulkhead. (b) Connect a 52-inch length of 0.25-inch O.D. by 0.040-inch wall polyethylene tubing to the static line running under the floorboard with a 262-P-1/4 union. (c) Place the pack nut and plastic ferrule not used with the union on the other end of the tubing and connect the tee fitting. (d) Remove the clips which originally secured the static lines to the cabin bulkhead and use one to attach the static line to the top of the bulkhead just aft of the cabin bulkhead Station 239.00. (e) Shorten the tubing from each static port to provide gentle curves and to prevent any low places in the line that could trap water between the static ports and the tee. Reconnect the two shortened static port lines to the tee fitting using either the original plastic ferrules and pack nuts or new like parts. (Beech Service Bulletin No. 7 covers this same subject.) This directive effective June 19, 1965.
2018-13-01: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) model 250-C turboshaft engines. This AD was prompted by several reports of engine power loss, one of which resulted in a fatal helicopter accident. This AD requires removal of the power turbine governor (PTG) bearing assembly, part number (P/N) 2544198, and its replacement with a bearing assembly eligible for installation. We are issuing this AD to address the unsafe condition on these products.
89-07-13: 89-07-13 BOEING: Amendment 39-6165. \n\tApplicability: Model 737 series airplanes, certificated in any category. \n\n\tCompliance: Required within the next 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent smoke in the cockpit and partial loss of electrical power caused by the failures of the Generator Control Unit (GCU) filter modules, accomplish the following: \n\n\tA.\tReplace or modify the GCU filter modules, in Westinghouse GCU P/N 915F212- 5 and GCU P/N 948F458-1, in accordance with Westinghouse Service Bulletin 87-101, dated March 1987, or Westinghouse Service Bulletin 87-102, dated August 1987. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who mayadd any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Westinghouse, Electrical Systems Division, P.O. Box 989, Lima, Ohio 45802. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, FAA, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6165, 89-07-13) becomes effective on April 28, 1989.