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2022-14-03: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by reports of cracked tailboom attachment bolts and barrel nuts. This AD requires replacing the upper left hand (LH) tailboom attachment bolt, visually inspecting the other three tailboom attachment bolts and all barrel nuts, repetitive torque checks of the tailboom attachment bolts, and corrective action if necessary, 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.
99-11-03: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA341G and SA342J helicopters. This action requires, before further flight, visually inspecting the external body of each main rotor head pitch-change rod (rod) for corrosion. If external corrosion is found, this action also requires a visual inspection of the inside of the body of that rod for corrosion. A rod with external corrosion that exceeds the repair criteria or a rod with any internal corrosion must be replaced with an airworthy rod. This amendment is prompted by the report of a deep internal corrosion fault in a rod found by a military helicopter operator performing a daily inspection. This condition, if not corrected, could result in failure of a rod and subsequent loss of control of the helicopter.
99-11-02: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney R-1340 series reciprocating engines, that requires initial and repetitive visual and fluorescent penetrant inspections of cylinders for head cracking. This amendment is prompted by reports of cylinder head cracking. The actions specified by this AD are intended to prevent cylinder head cracking, which can result in engine power loss, forced landing, and damage to the aircraft.
81-16-03: 81-16-03 DOWTY ROTOL LTD.: Amendment 39-4171. Applies to Dowty Rotol propellers Type R175/4-30-4/13E with hub and driving assembly, P/Ns 601022104 or 601022420 which do not have Dowty Rotol Service Bulletin 61-604 (Mod. No. (c)VP2388) incorporated, as installed on, but not limited to Fairchild F-27, F-27B, and Fokker F-27 Mks 100, 300 and 700 airplanes. Compliance is required as indicated, unless already accomplished To prevent propeller failure due to cracking of the propeller hub, accomplish the following repetitive actions until modified in accordance with paragraph (d) below: (a) Propeller hubs with less than 20,000 total hours time in service, inspect in accordance with paragraph (c) at next overhaul or prior to accumulating 22,000 total hours, whichever occurs first, and reinspect in accordance with paragraph (c) at each subsequent overhaul. If an operator finds a cracked hub in his fleet, the reinspection interval must not exceed 2,000 operating hours on allof his propellers that exceed 20,000 total hours. (b) Propeller hubs with 20,000 or more total hours time in service, inspect as follows: (1) Hubs with more than 1400 hours since last inspection or overhaul, inspect in accordance with paragraph (c) prior to accumulating 600 additional operating hours after the effective date of this AD and reinspect in accordance with paragraph (c) at each subsequent overhaul. If an operator finds a cracked hub in his fleet, the reinspection interval must not exceed 2,000 operating hours on all of his propellers that exceed 20,000 total hours. (2) Hubs with less than 1400 hours since last inspection or overhaul, inspect in accordance with paragraph (c) prior to accumulating 2000 hours since last inspection or overhaul and reinspect at each subsequent overhaul. If an operator finds a cracked hub in his fleet, the reinspection interval must not exceed 2,000 operating hours on all of his propellers that exceed 20,000 total hours. (c) Inspection Procedure: (1) During overhaul or propeller disassembly, crack test the hub front wall to snout radius in accordance with Part 2A of Dowty Rotol Service Bulletin No. 61-909 dated September 19, 1978, as revised March 12, 1979, or FAA approved equivalent. If cracks are found, replace the cracked hub with a hub known to be free of cracks. (2) For propellers between overhauls, remove, disassemble, inspect, reassemble and reinstall in accordance with Part 2B of Dowty Rotol Service Bulletin No. 61-909 dated September 19, 1978, as revised March 12, 1979, or FAA approved equivalent. If cracks are found during inspection, additional propeller disassembly is necessary to replace the cracked hub with a hub known to be free of cracks, and testing and rebalancing and resetting blade angles is necessary. (d) Terminating Action: The inspections required by this AD may be discontinued when propellers are modified by Dowty Rotol Service Bulletin 61-604 (Mod. No. (c)VP2388) dated July 1968 as revised by Revision 2 dated November 24, 1971, or FAA approved equivalent. Upon request of an operator, the Chief, Engineering and Manufacturing Branch, AGL- 210, Federal Aviation Administration, Great Lakes Region, may adjust the compliance time specified in paragraph (a) of this AD provided such requests are made through an FAA maintenance inspector, and the request contains substantiating data to justify the request for that operator. For purposes of this AD, an FAA approved equivalent must be approved by the Chief, Engineering and Manufacturing Branch, AGL-210, Federal Aviation Administration, Great Lakes Region. The manufacturer's specifications and procedures identified in the directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer may obtain copies upon request to Dowty Rotol, Inc., Staverton West, Sully Road, Box 5000, Sterling, VA 22170 or Dowty Rotol, Ltd., Cheltenham Road, Gloucester, England GL2 9QH. These documents may also be examined at the Great Lakes Region, FAA, 2300 East Devon Avenue Des Plaines, Illinois 60018. This amendment becomes effective July 28, 1981.
74-07-01: 74-07-01 BELL: Amendment 39-1801 as amended by Amendment 39-1864. Applies to all cyclic and collective main rotor control tube assemblies installed within a 30 degree angle of the vertical axis on Model 47 series helicopters, certificated in all categories. Compliance required within the next 100 hours time in service after the effective date of this A.D., unless already accomplished, and thereafter at intervals not to exceed 1200 hours time in service from the last inspection. To detect corrosion and prevent possible failure of the control tube assemblies, accomplish the following inspection. (a) Remove the control tube assemblies from the helicopter and remove the rod end bearing and insert or clevis at each end of the tube assembly and clean the inside of the tube. (b) Inspect each control tube for internal corrosion using a light and borescope or equivalent inspection means. (c) Remove corroded control tubes from service prior to further flight, exceptas specified by paragraph (g) of this A.D. and submit a report of finding a corroded tube to Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA, P.O. Box 1689, Fort Worth, Texas, 76101. The control tube assembly part number, degree of corrosion found and total time in service should be included in the report. FAA Form 8330-2 may be used for this report. (Reporting approved by the Bureau of the Budget under BOB No. 04- R0174.) (d) Reinstall serviceable rod end bearings and inserts or clevis in the uncorroded and serviceable tubes using acceptable techniques, methods and practices as specified below. (1) Tubes with double drilled rivet holes, sharp nicks or scratches and internal corrosion are considered unserviceable. (2) Tubes must have internal corrosion protection using zinc chromate primer, hot linseed oil or other equivalent corrosion inhibitor. The tube ends must be sealed, air and water tight, as specified in Paragraphs 4 and 5, Part II, Bell Helicopter Company Service Bulletin No. 47-11-73-1, Rev. A, dated December 6, 1973 or later approved revision or as specified in an equivalent FAA approved procedure when the insert, rod end bearing or clevis and rivets are installed. (e) Install control tube assemblies on the helicopter and check the controls rigging and check tracking of the main rotor blades in accordance with pertinent Model 47 maintenance and overhaul information manual. (f) 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 the Service Manager, Bell Helicopter Company, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D. C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D. C., and at the Southwest Regional Office in Fort Worth, Texas. (Bell Helicopter Company Service Bulletin No. 47-11-73-1, Rev. A, dated 12-11-73 pertains to this subject.) (g) Tubes with light corrosion over less than twenty-five percent of the area in any one-half inch length of the tube may be returned to service provided the tube is assembled and protected as noted in paragraph (d) of this A.D. and the tube is removed from service prior to accumulating 200 hours time in service after the initial inspection prescribed by this A.D. was conducted. NOTE: Advisory Circular No. 43-4, page 47 defines light corrosion. Amendment 39-1801 became effective April 22, 1974. This Amendment 39-1864 becomes effective May 30, 1974.
85-07-03 R1: 85-07-03 R1 SPERRY FLIGHT SYSTEMS, AVIONICS DIVISION: Amendment 39-5026 as amended by Amendment 39-5411. Applies to Sperry Model SPZ-7000 with FZ-700 computer Part No. 7003183-901 or 7003183-902 installed. The SPZ-7000 installation is known to exist on, but may not be limited to, Sikorsky Model S-76A helicopters modified in accordance with Supplementary Type Certificate (STC) No. SH2218NM, and S.N.I.A.S. Model AS-365N helicopters modified in accordance with STC No. SH2215NM. Compliance is required within ten (10) days after the effective date of this AD, unless previously accomplished. To prevent improper (dangerous) excursions from the glide slope during instrument landing system (ILS) approach, accomplish the following: A. Install a placard adjacent to the autopilot/flight director mode selector in full view of pilot, stating "DO NOT ENGAGE ILS MODE ABOVE 2000 FEET AGL DURING ILS APPROACH." B. Installation of FZ-700 computers, Part Number (P/N) 7003138-902 with modification "E" incorporated, on Sikorsky S-76A helicopters; or P/N 7003138-901 with modification "F" incorporated, on S.N.I.A.S. Model AS-365N helicopters; constitutes terminating action for the requirement of paragraph A. of this AD. C. Alternate modifications or other actions which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Sperry Corporation, Aerospace and Marine Group, P.O. Box 29000, Phoenix, Arizona 85038. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California. Amendment 39-5206 became effective April 15, 1985. This amendment, 39-5411, becomes effective September 14, 1986.
2013-22-09: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by reports of movement of the rudder pedals being impeded due to corrosion of the trunnion shaft of the rudder feel trim unit (RFTU). This AD requires an inspection to determine if certain RFTUs are installed, an operational check for signs of seizure of affected parts, repetitive lubrication of certain RFTUs, and replacement of the RFTU if necessary. Installing replacement RFTUs having conformal bushings terminates the repetitive lubrication requirements. We are issuing this AD to detect and correct any sign of rough movement or seizure of the trunnion shaft and its bushing, which could cause a rudder control jam or a large and rapid alternating rudder input leading to a structural failure of the vertical fin.
99-10-14: 99-10-14 BOEING: Amendment 39-11167. Docket 98-NM-232-AD. Supersedes AD 98-14-10, Amendment 39-10643. \n\n\tApplicability: Model 747-400, 757, 767, and 777 series airplanes; equipped with AlliedSignal RIA-35B Instrument Landing System (ILS) receivers, part number (P/N) 066-50006-0101, certificated in any category. \n\n\tNOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent erroneous localizer deviation provided by faulty ILS receivers, which could result in a landing outside the lateral boundary of the runway, accomplish the following: \n\nRestatement of the Requirements of AD 98-14-10 \n\n\t(a)\tWithin 10 days after July 22, 1998 (the effective date of AD 98-14-10, amendment 39-10643), revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD into the AFM.\n \n\t"Any Instrument Landing System (ILS) or Localizer approach with only one operative AlliedSignal LS receiver, P/N 066-50006-0101, installed is prohibited." \n\n\tNOTE 2: On Model 747-400 and 777 series airplanes, the existence of only one operative ILS receiver is indicated by the Engine Indication and Crew Alerting System advisory message, "SNGL SOURCE ILS." On Model 757 and 767 series airplanes, failure of an ILS receiver is indicated by an ILS flag on the display of the Electronic Flight Instrument System when approach mode is selected. \n\n\t(b)\tWithin 30 days after July 22, 1998, accomplish the requirements of either paragraph (b)(1) or (b)(2) of this AD. \n\n\t\t(1)\tPerform a visual inspection of the 64 flight legs of the internal fault memory of all AlliedSignal RIA-35B ILS receivers, P/N 066-50006-0101, for fault codes "Nl" (glide slope antialias fault) or "Nm" (localizer antialias fault). Repeat the inspection thereafter at intervals not to exceed 64 flight cycles. If any fault code "Nl" or "Nm" is found, prior to further flight, replace the existing ILS receiver with a new or serviceable ILS receiver having the same P/N; or with an ILS receiver that has been modified to P/N 066-50006-1101 in accordance with AlliedSignal Electronic and Avionics Systems Service Bulletin M-4426 (RIA-35B-34-6), Revision 3, dated May 1998. Installation of an ILS receiver that has been modified (and the P/N converted) in accordance with the service bulletin constitutes terminating action for the inspection requirement of paragraph (b)(1) of this AD for that part. \n\n\t\t(2)\tAccomplish the actions required by paragraphs (b)(2)(i) and (b)(2)(ii) of this AD. \n\n\t\t\t(i)\tRevise the Limitations Section of the FAA-approved AFM to include the following statement. This may be accomplished by inserting a copy of this AD into the AFM. \n\n\t"Category II and III operations are prohibited with AlliedSignal ILS receiver P/N 066-50006-0101 installed." \n\n\t\t\t(ii)\tInstall a placard on the forward instrument panel of the cockpit in clear view of the pilots, which states: \n\n\t\t"Category II and III operations are prohibited." \n\n\t(c)\tAs of July 22, 1998, no person shall install on any airplane an RIA-35B ILS receiver, P/N 066-50006-0101, that has been found to be discrepant (that is, on which fault codes "Nl" or "Nm" were found during an inspection of the internal fault memory) unless the discrepancy has been corrected by modifying the ILS receiver in accordance with AlliedSignal Electronic and Avionics Systems Service Bulletin M-4426 (RIA-35B-34-6), Revision 3, dated May 1998. \n\nNew Requirements of This AD \n\n\t(d)\tWithin 6 months after the effective date of this AD, replace all existing RIA-35B ILS receivers, P/N 066-50006-0101, with RIA-35B ILS receivers that have been modified in accordance with AlliedSignal Electronic and Avionics Systems Service Bulletin M-4426 (RIA-35B-34-6), Revision 3, dated May 1998; and that have had their P/N's converted to 066-50006-1101. Such replacement constitutes terminating action for the requirements of this AD. After the replacement has been accomplished, the AFM limitations required by paragraphs (a) and (b)(2)(i) of this AD may be removed from the AFM, and the placard required by (b)(2)(ii) may be removed from the cockpit. \n\n\tNOTE 3: Modification of all AlliedSignalRIA-35B ILS receivers, P/N 066-50006-0101, prior to July 22, 1998, in accordance with AlliedSignal Electronic and Avionics Systems Service Bulletin M-4426 (RIA-35B-34-6), dated December 1997; Revision 1, dated January 1998; or Revision 2, dated April 1998; is considered acceptable for compliance with the applicable action specified in this amendment. \n\nAlternative Methods of Compliance \n\n\t(e)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\nSpecial Flight Permits \n\n\t(f)\tSpecial flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. \n\nIncorporation by Reference \n\n\t(g)\tThe modification shall be done in accordance with AlliedSignal Electronic and Avionics Systems Service Bulletin M-4426 (RIA-35B-34-6), Revision 3, dated May 1998. The incorporation by reference of this document was approved previously by the Director of the Federal Register as of July 22, 1998 (63 FR 36549, July 7, 1998). Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\t(h)\tThis amendment becomes effective on June 17, 1999.
88-03-52: 88-03-52 PRATT & WHITNEY: Amendment 39-5957. Final copy of Telegraphic AD. Applies to Pratt & Whitney (PW) PW2037 and PW2040 turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent compressor and turbine case cooling air valve tube and 2.5 bleed valve actuator tube cracking that can lead to fuel leaks, substantial fuel quantity loss and possible engine fire, accomplish the following: (a) For the engines operated in any of the following configurations: (1) with the Fuel Quantity Indication System (FQIS) inoperative under the provisions specified in the Boeing 757 aircraft Master Minimum Equipment List (MMEL), Item 28-41-1; (2) with one of the Fuel Quantity Processor (FQP) Channels inoperative under the provisions specified in the MMEL, Item 28-41-2; (3) with both Flight Management Computer (FMC) Systems inoperative under the provisions specified in the MMEL, Item 34-61-1; or (4) with the FQIS functional, both FQP Channels functional, and at least one FMC System functional, but operating without the provisions of Boeing Operations Manual Bulletin (OMB) Number 87-7, Revision 1, dated October 28, 1987, accomplish the following prior to further flight: (a)(i) Compressor and turbine case cooling air valve tube clamping configuration: Remove loop clamp bracket assembly Part Number (P/N) 1B2224-01 from compressor and turbine case cooling air valve tubes, and install a clamping configuration that clamps the tubes to a bracket spanning the pressure and return tubes in accordance with Accomplishment Instructions contained in PW Alert Service Bulletin (ASB) Number PW2000 A75-36, dated October 28, 1987. (a)(ii) 2.5 bleed valve actuator tubes and manifold assembly clamping configuration: Install a new bracket and clamp configuration in accordance with the applicable part of the Accomplishment Instructions contained in PW ASB Number PW2000 A75-38, dated December 21, 1987. (b) For engines operated with the FQIS functional, both FQP Channels functional, at least one FMC System functional, and in accordance with the provisions of Boeing OMB Number 87-7, Revision 1, dated October 28, 1987, accomplish items (a)(i) and (a)(ii) above within 250 hours in service from the effective date of this AD. (c) 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. (d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. (e) Upon submission of substantiating data by an owner or operator through an FAA airworthiness inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. Pratt & Whitney ASB's NO. PW2000 A75-36, dated October 28, 1987, and NO. PW2000 A75-38, dated December 21, 1987, 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 the engine manufacturer's ASB's may obtain copies upon request to Pratt & Whitney, Publication Department, P.O. Box 611, Middletown, Connecticut 06457. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 88-ANE-02, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5957, becomes effective on July 13, 1988, as to all persons except those persons to whom it was made effective 24 hours after receipt by individual Telegraphic AD T88-03-52, issued January 29, 1988, which contained this amendment.
91-07-18: 91-07-18 ING. HEINO BRDITSCHKA FLUGTECHNIK GES.M.B.H (HB AIRCRAFT INDUSTRIES AG): Amendment No. 39-8089. Docket No. 91-CE-32-AD. Applicability: Models HB-23/2400-SP powered gliders (all serial numbers), HB-23/2400 and HB-23/2400 Scanliner and Hobbyliner powered gliders that are equipped with a three-blade adjustable propeller, certificated in any category. Compliance: Required prior to further flight after the effective date of this AD, unless already accomplished. To prevent loss of the propeller while in flight that could result in damage to the powered glider and loss of control, accomplish the following: (a) Replace the three-blade propeller with a fixed-pitch, two-blade propeller in accordance with Ing. HB Instructions 23/2/90, dated December 19, 1990. (b) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe,Africa, Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (c) The inspections and replacements required by this AD shall be done in accordance with Ing. HB Instructions 23/2/90, dated December 19, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. Section 552(a) and 1 CFR Part 51. Copies may be obtained from Ing. Heino Brditschka Flugtechnik Ges.m.b.H. (HB Aircraft Industries AG), Dr. Adolf Scharfstr. 44, 4053 Haid, Austria. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-8089, AD 91-07-18) becomes effective onJanuary 3, 1992, as to all persons except those persons to whom it was made immediately effective by priority letter AD 91-07-18, issued March 29, 1991, which contained this amendment.