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2016-16-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by reports of fatigue cracks in the station 320 crown frame and in window post number 3. This AD requires repetitive inspections for cracks and missing fasteners of the station 320 crown frame, cracks in the web and flange surfaces of the forward segment of window post number 3, and missing fasteners and cracks of the window upper sill; post-modification inspections for cracks of the window upper sill; a one-time fastener rework; and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking and missing fasteners of the station 320 crown frame, cracking of the window post number 3, and cracking of the window upper sill, which could result in an in-flight decompression and a loss of structural integrity of the fuselage.
72-23-02: 72-23-02 ROLLS ROYCE (1971) LTD: Amendment 39-1547. Applies to Rolls Royce Dart Models 542-4, -4K, -10, -10J, and -10K engines. These engines are installed on, but not necessarily limited to, Convair 340/440 airplanes that have had subject engines installed by modification, and NAMC YS-11 and YS-11A airplanes, all series. (NOTE: Subject Convair 340/440 airplanes are also known as Convair 600 and 640 airplanes.) Compliance is required as indicated. To prevent damage to the rear face of the first stage impeller that could lead to impeller disintegration in service, accomplish the following: (a) Within the next 300 flights after the effective date of this AD, or before the accumulation of 2,000 flights on the compressor since installed new or since last compressor overhaul, as applicable, whichever occurs later, unless already accomplished, modify the oil drain plug, P/N RK.35189, and refit it to the engine in accordance with Rolls Royce Dart Aero Engine Service Bulletin Number DA 72-383, Revision 1, dated November 30, 1971, or an FAA-approved equivalent. Identify the modified drain plug as P/N RK. 46404. (b) Within the next 300 flights after incorporation of the modification specified by paragraph (a), and thereafter at intervals not to exceed 300 flights from the last inspection visually inspect the surfaces of the drain plug, P/N RK.46404, for the presence of aluminum particles. If aluminum particles are found during an inspection required by this paragraph, before further flight comply with paragraph (e). NOTE: During inspections required by paragraph (b) particular attention should be directed to the sealing ring recess. (c) For an engine that is subject to an FAA-approved continuous airworthiness maintenance program that includes periodic inspection for freedom of engine rotation and periodic inspection of the oil filter, comply with the following: (1) At each inspection for freedom of engine rotation, listen for unusualnoises from the compressor area; and (2) At each inspection of the oil filter, visually inspect the filter for traces of fine aluminum dust in the bottom of the filter cap or in suspension in the residual oil in the filter cap. (3) If any unusual noise emanates from the compressor area during an inspection required by subparagraph (c) (1) or if any trace of fine aluminum dust is found during an inspection required by subparagraph (c) (2), before further flight comply with paragraph (e). Change to an approved program that affect either the interval or performance of inspections required by this AD must be approved by the assigned FAA Maintenance Inspector. (d) For engines that are not subject to an FAA-approved continuous airworthiness maintenance program that includes periodic inspection for freedom of engine rotation and periodic inspection of the oil filter comply with the following: (1) At each inspection required by paragraph (b) - (i) Inspect thefirst stage impeller for freedom of rotation by rotating it at least one full turn in each direction, and listen for unusual noises from the compressor area. (ii) Visually inspect the oil filter for traces of fine aluminum dust in the bottom of the filter cap or in suspension in the residual oil in the filter cap. (2) If the first stage impeller does not rotate freely in each direction or if any unusual noise emanates from the compressor area during an inspection required by subparagraph (d)(1)(i), or if any trace of fine aluminum dust is found during an inspection required by subparagraph (d)(1)(ii), before further flight comply with paragraph (e). (e) Remove one combustion chamber and visually inspect the compressor outlet elbow, flame tube, discharge nozzle, H.P. nozzle guide vanes, and H.P. turbine blades for evidence of metal spatter and surface roughness or impact damage due to the passage of a foreign object. If any of these indications are found, before further flight rebuild the engine in accordance with Rolls Royce Dart Aero Engine Service Bulletin Da 72-383, Revision 1, dated November 30, 1971, or an FAA-approved equivalent. (f) For the purpose of complying with this AD, a flight is an operating sequence consisting of an engine start, takeoff operation, landing, and engine shutdown. The number of flights may be determined by actual count or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing the compressor section's time in service by the operator's fleet average time for airplanes equipped with the subject type engines. (g) At the request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East 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 that operator. (h) The repetitive inspections required by this AD may be discontinued on engines that have been rebuilt in accordance with paragraph (e). This amendment supersedes Amendment 39-1381 (37 F.R. 666), AD 72-02-04. This amendment becomes effective October 26, 1972.
71-02-04: 71-02-04 BOEING: Amdt. 39-1146. Applies to all Boeing Model 747 Series airplanes. \n\tCompliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent the failure of the load evener indicator tube resulting in passenger injury: \n\tReplace the existing body gear indicator tube cover with a new tube cover in accordance with Boeing Service Bulletin 32-2031, dated July 24, 1970, or later FAA approved revision, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\tThis amendment becomes effective January 23, 1971.
2005-15-06: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200C and 747-200F series airplanes. This AD requires one-time inspections for cracks and material loss in the fuselage skin above the stringer (STR) 23 lap splice, between Body Station (BS) 282 and BS 298, and repair if necessary. This AD is prompted by a report of a crack above the STR 23 lap splice on one airplane. We are issuing this AD to detect and correct cracks or material loss in the fuselage skin, and consequent reduced structural integrity of the skin panel, which could result in rapid depressurization of the airplane.
84-18-05: 84-18-05 FOKKER VFW B.V.: Amendment 39-4911. Applies to all Model F27 Series airplanes, serial numbers 10102 to 10611, inclusive, that are equipped with pylon tanks and the maximum certificated takeoff weight is above 41,000 pounds, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent wing structural failure, accomplish one of the following (A, B, or C): A. Within the next 100 hours time in service after the effective date of this airworthiness directive (AD): 1. Remove the existing airspeed limitation placards and install new placards in accordance with paragraph 2.A and 2.B of the Accomplishment Instructions of Fokker Service Bulletin No. 11/3 dated October 1, 1981. 2. Incorporate changes to the FAA approved Airplane Flight Manual in accordance with paragraphs 1.C and 3 of Fokker Service Bulletin No. 11/3 dated October 1, 1981. 3. Modify the airspeed indicators and overspeed aural warning system to provide a switchable maximum operating speed (VMO) that allows selecting a VMO of 204 knots I.A.S. for operation when the maximum takeoff weight exceeds 41,000 pounds, in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. B. Within the next 100 hours time in service after the effective date of this AD, modify as follows: 1. Revise the redline marking of the airspeed indicator or replace the airspeed indicator to reflect the new maximum airspeed limitation of 204 knots I.A.S. 2. Post a placard on the left and right hand instrument panel to read as follows: "MAXIMUM AIRSPEED, 204 KIAS." 3. Adjust the overspeed aural warning device or install a new device so as to comply with the new maximum airspeed limitation; i.e., 204 knots I.A.S., within the tolerances specified by FAR 25.1303(c)(1). C. Apply for and obtain a supplement to the Airplane Flight Manual which will provide for an operating limitation of 41,000 pounds takeoff weight. Applications may be made to the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. 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 modifications required by this AD. This amendment becomes effective October 15, 1984.
87-03-03: 87-03-03 BRITISH AEROSPACE: Amendment 39-5504. Applies to Model 3101 Jetstream (S/N 642 to 646, 648 to 655, 657, 658 and 660 to 666 inclusive) airplanes certificated in any category. Compliance: Required within 600 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To ensure operation of fuel/hydraulic and water methanol system valves during critical flight operations, accomplish the following: (a) Modify the HiTemp Valves Part Number (P/N) HTE 4925-001 as follows: (1) Gain access to the valves in accordance with Section 2. "ACCOMPLISHMENT INSTRUCTIONS", paragraph A PREPARATION", in British Aerospace (BAe) S/B 28-JA850911 dated June 13, 1986. (2) Replace valve spindles P/N 4925-005 with strengthened spindles P/N 4925-013 in HiTemp Model HTE 1" Actuated Ball Valves in accordance with Section 2. "ACCOMPLISHMENT INSTRUCTIONS" in HiTemp SB HTE 4925/1-SB-1 dated August 19, 1985, on those valves located as follows:(i) Fuel system - left and right LP cocks at wing leading edges outboard of the engines, and crossfeed cock on fuselage center section. (ii) Hydraulic System - left and right LP cocks in the hydraulic installations below fuselage center section. (iii) Water Methanol System (if fitted) - stop valves in the left and right main landing gear bays. (3) Carry out functional tests of the valves in accordance with Section 2. "ACCOMPLISHMENT INSTRUCTIONS", paragraph B "ACCOMPLISHMENT", in BAe S/B 28-JA850911 dated June 13, 1986. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000, Brussels, Belgium. All persons affected by this directive may obtain a copy of the document referredto herein upon request to British Aerospace plc, Manager, Product Support Civil Aircraft Division, Prestwick Airport, Ayrshire, KA9 2RW, Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on February 17, 1987.
2005-13-22: The FAA is superseding an existing airworthiness directive (AD) that applies to all EMBRAER Model EMB-135 and -145 airplanes. The existing AD currently requires repetitive inspections of the electrical connectors of the electric fuel pumps to detect discrepancies, application of anti-corrosion spray, replacement of all fuel pumps with improved fuel pumps, repetitive inspections after all six fuel pumps are replaced, and applicable corrective actions. This new AD retains those requirements but revises the initial compliance time for an inspection for certain airplanes. This new AD is prompted by the need to correct a compliance time in the existing AD. We are issuing this AD to prevent an ignition source in the fuel tank or adjacent dry bay, which could result in fire or explosion. DATES: Effective July 7, 2005. On May 19, 2005 (70 FR 19685, April 14, 2005), the Director of the Federal Register approved the incorporation by reference of EMBRAER Service Bulletin 145-28-0013, dated April 25, 2001. On October 3, 2000 (65 FR 56233, September 18, 2000), the Director of the Federal Register approved the incorporation by reference of EMBRAER Alert Service Bulletin S.B. 145-28-A013, dated August 16, 2000. We must receive any comments on this AD by August 22, 2005.
2005-15-02: The FAA is adopting a new airworthiness directive (AD) that applies to certain Airbus Model A320-111 airplanes and Model A320-200 series airplanes. This AD requires post-maintenance bleeding of accumulated air from, or ground functional testing of, the ram air turbine (RAT) system; modifying and reidentifying the airborne ground check module of the RAT system; and replacing the RAT reducer assembly if applicable. This AD is prompted by reports of unsuccessful in-flight RAT tests during which a deployed RAT failed to pressurize the blue hydraulic circuit of the RAT system. We are issuing this AD to prevent failure of the RAT during an in-flight emergency, which could lead to loss of hydraulic and electrical power and reduced controllability of the airplane.
2016-14-01: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 Freighter series airplanes; Model A330-200 and A330-300 series airplanes; Model A340-200 and A340-300 series airplanes; Model A340-500 series airplanes; and Model A340-600 series airplanes. This AD was prompted by a report indicating that, during an operational test of a ram air turbine (RAT), the RAT did not deploy in automatic mode. This AD requires identification of the manufacturer, part number, and serial number of the RAT, and re-identification and modification of the RAT if necessary. We are issuing this AD to prevent non-deployment of the RAT, which, if preceded by a total engine flame- out, or during a total loss of normal electrical power generation, could result in reduced control of the airplane.
71-21-07: 71-21-07 de HAVILLAND: Amendment 39-1310. Applies to de Havilland Model DHC- 6 Airplanes, Serial Numbers 6 through 289 certificated in all categories and incorporating Flitetronic Type PC 15 or PC 15A Inverters. Compliance required within the next 250 hours' time in service after the effective date of this AD unless already accomplished. To prevent a total loss of AC power in the event of a fault occurring in an AC circuit, accomplish the following: (a) Comply with Accomplishment Instructions 1 and 2 (a) through 2(e) of de Havilland Service Bulletin No. 6/263 dated 5 October 1970, Revision B dated 29 January 1971. (b) Remove slow-blow fuses not replaced in (a) and replace with: (1) Littlefuse type 312 of the same rating for the 26-volt supply except that ratings greater than 2 amps shall be replaced with Littlefuse 312002. (2) Littlefuse type 312 or Bussman type MB of the same rating for the 115 Volt supply, except that ratings greater than 1 amp shallbe replaced with Littlefuse 312001 or Bussman MB01. (c) Comply with Accomplishment Instructions 3 through 6 of de Havilland Service Bulletin No. 6/263 dated 5 October 1970, Revision B dated 29 January 1971 for PC 15 and PC 15A inverter without a suffix letter after the serial number. Inverters which do not meet the requirements of the overload function test must be replaced, prior to further flight, with an inverter with a suffix letter after the serial number. Equivalent methods may be used provided they are approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Upon request with substantiation data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective October 12, 1971.
89-18-05: 89-18-05 BRITISH AEROSPACE: Amendment 39-6298. (Docket No. 89-NM-53-AD) Applicability: Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent uncommanded thrust reverser selection, accomplish the following: A. Prior to the accumulation of 1,500 landings or within 3 months after the effective date of this AD, whichever occurs first, inspect the thrust reverser cables to determine correct installation, in accordance with British Aerospace Alert Service Bulletin 76-A-PM5978, Issue No. 1, dated November 14, 1988. B. If thrust reverser cables are found to be worn or damaged, or if cables are found to be incorrectly routed, replace prior to further flight, in accordance with the maintenance manual referenced in British Aerospace Alert Service Bulletin 76-A-PM5978, Issue No. 1, dated November 14, 1988. 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 in order to comply with 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, Librarian for Service Bulletins, 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 the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6298, AD 89-18-05) becomes effective on September 21, 1989.
74-21-04: 74-21-04 HUGHES HELICOPTERS: Amendment 39-1987 as amended by Amendment 39-2147. Applies to Hughes 269A, 269A-1, 269B, 269C Helicopters certificated in all categories, including military TH-55A equipped with canopy slat P/N 269A2297 or 269A2297-7. Compliance required as indicated. To detect possible cracks in canopy slat surfaces, and the condition and security of slat attachment hardware and canopy attachment areas, and provide for modification of the canopy slat, accomplish the following: (a) On each day the helicopter is flown, conduct a close visual check by the pilot in command or an inspection by a certificated mechanic of the canopy slat surfaces over the entire length for cracks, slat attachment hardware and canopy attachment areas for condition and security. Note: The person who performs the check or inspection shall record it in the appropriate aircraft records per FAR 91.173. (1) If cracks or other damage are found, replace prior to further flight with: (i) P/N 269A2297 or 269A2297-7 modified in accordance with (b), below; or (ii) P/N 269A2214; or (iii) If the 50 hour limitation specified by (b), below, has not been exceeded, an unmodified part P/N 269A2297 or 269A2297-7 may be used, provided, it is modified at the time specified by (b), below; or (iv) A part approved by Chief, Aircraft Engineering Division, FAA Western Region. (b) Prior to the next 50 hours time in service after the effective date of this amendment, 39-2147, unless already accomplished, modify the canopy slat, P/N 269A2297 or 269A2297-7, in accordance with the instructions contained in Hughes Service Information Notice N-127, dated March 5, 1975, or later FAA-approved revisions, or equivalent procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Upon installation of P/N 269A2297 or 269A2297-7 modified in accordance with (b), above, or P/N 269A2214 or other part approved by the Chief, AircraftEngineering Division, FAA Western Region, the daily visual check or inspection in accordance with (a) above may be discontinued. Amendment 39-1987, was effective October 16, 1974, for all persons except those to whom it was made effective immediately by airmail letter dated September 23, 1974. This Amendment 39-2147, to AD 74-21-04 becomes effective April 4, 1975.
70-01-02: 70-01-02 CESSNA: Amdt. 39-906. Applies to Models 177 and 177A, Serial Numbers 177- 00001 thru 177-01160, 177-01165 thru 177-01168, 177-01171, 177-01174 thru 177-01178 and 177-01180, airplanes. Compliance: Required as indicated, unless already accomplished. To prevent possible damage to the fuel quantity transmitter float arm during refueling, which can result in inaccurate quantity indication, accomplish the following: Within 50 hours' time in service after the effective date of this AD but no later than March 1, 1970, remove the fuel quantity transmitter from each fuel tank and install new Cessna P/N 12341-667-1 and 12341-667-2 fuel gauge transmitters in accordance with the instructions contained in Cessna Service Letter No. SE69-25. dated December 9, 1969, or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective January 3, 1970.
2005-14-12: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. models HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC- B3MN-3, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, HC-B4MP-3, HC-B4MP-5, and HC- B5MP-3 propellers, installed with propeller mounting bolts, part number (P/N) B-3339. This AD requires initial and repetitive visual inspections and torque checks of certain manufacture lot numbers of propeller mounting bolts, P/N B-3339, and eventual removal from service of those bolts. This AD results from the discovery during routine propeller installation that a bolt from a certain manufacture lot did not properly absorb the installation torque. This AD also results from the discovery that other bolts of the same part number from a different manufacture lot had material surface pitting. We are issuing this AD to prevent propeller attaching bolt failures or improperly secured propellers, which could lead to separation of the propeller from the airplane.
2016-15-02: We are adopting a new airworthiness directive (AD) for all M7 Aerospace LLC Models SA26-AT, SA26-T, SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes. This AD was prompted by reports of multiple cracks in the steel horizontal tube of the cockpit control column. This AD requires inspection of the cockpit control column horizontal tube for cracks and repair or replacement of the cockpit control column as necessary. We are issuing this AD to correct the unsafe condition on these products.
73-07-07: 73-07-07 CESSNA: Amdt. 39-1617. Applies to all Models 310 and 320 series airplanes and Serial Numbers, except Models 310, 310A, 310B and 310Q (Serial Numbers 310Q0710 and up). Compliance: Required as indicted, unless already accomplished. To determine condition of fuel lines, electrical wiring, and to detect loose fittings and attachments, to reduce possible collection of flammable fluids and to eliminate possible ignition sources within the leading edges of the wings, within the next 25 hours' time in service after the effective date of this AD, accomplish the following in accordance with Cessna Multi-engine Service Letter ME73-5 dated March 16, 1973, and Cessna Service Kit SK310-90 dated March 7, 1973, or later FAA approved revisions or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region: 1) Inspect the fuel lines and electrical harnesses in the wing leading edge for corrosion, chafing, looseness, or other unserviceable conditions. Procedures for this inspection are contained in Cessna Service Kit SK 310-90. 2) Prior to further flight replace and/or repair any unserviceable parts or conditions found as result of the above inspection. 3) Install leading edge drainage and sealant provisions in the wings in accordance with Paragraph B of Cessna Service Kit SK 310-90. 4) Remove, relocate and reinstall the auxiliary fuel boost pump resistor and relay in accordance with Paragraphs C and D of Cessna Service Kit SK 310-90. a) On those airplanes in which P/N 0850404-1 boost pump relay is installed, relocate this relay to wing trailing edge per Cessna Service Kit SK 310-90. (This relay is no longer eligible for installation in the wing leading edge. b) P/N FC 215-136 boost pump relay already installed in the wing leading edge is acceptable and as an alternative to Paragraph a), P/N 0850404-1 boost pump relay may be replaced with P/N FC 215-136 boost pump relay installed in the present wing leading edge location. c) On all airplanes relocate the boost pump resistor in accordance with Cessna Service Kit SK 310-90. 5) Place amended checklist entitled "Aircraft Fire Procedures Checklist" in the cockpit. This checklist is supplied with Cessna Service Kit SK 310-90. This amendment becomes effective April 6, 1973.
2005-14-06: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 707-300B, -300C, and -400 series airplanes. This AD requires repetitive inspections to detect cracked or broken hinge fitting assemblies of the inboard leading edge slats, and corrective action if necessary. This AD also provides as an option a preventive modification, which defers the repetitive inspections. In addition, this AD provides an option of replacing all hinge fitting assemblies with new, improved parts, which terminates the repetitive inspection requirements. This AD is prompted by results of a review to identify and implement procedures to ensure the continued structural airworthiness of aging transport category airplanes. We are issuing this AD to detect and correct fatigue cracking of the hinge fitting assembly of the inboard leading edge slats, which could result in reduced structural integrity of the slat system. This condition could result in loss of the inboard leading edge slat andcould cause the flightcrew to lose control of the airplane.
88-10-01: 88-10-01 BEECH: Amendment 39-5904. Applies to Models A23-24 and A24 (Serial Numbers (S/Ns) MA-1 through MA-368); Model A24R (S/Ns MC-2 through MC-95); Models A24R, B24R, and C24R (S/Ns MC-96 through MC-795), airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent reduction or loss of engine power due to fuel flow blockage resulting from broken electric fuel boost pump vanes in the engine driven fuel pump, accomplish the following: (a) For airplanes with 14 volt electrical systems, replace the existing electric fuel boost pump with a Beech P/N 1816-00-1 pump in accordance with the instructions in Beech Service Bulletin (MSB) No. 2217, dated February 1988. (b) For airplanes with 28 volt electrical systems, replace the existing electric fuel boost pump with a Beech P/N 1817-00-1 pump in accordance with the instructions in Beech MSB No. 2217,dated February 1988. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Department 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on June 6, 1988.
75-22-13: 75-22-13 LITTON SYSTEMS, INC., AERO PRODUCTS DIVISION: Amendment 39-2404. Applies to all LTN-72 inertial navigation systems installed on various airplane models, certificated in all categories, including, but not limited to, McDonnell Douglas DC-8 and DC-10 airplanes and Boeing 707 and 747 airplanes. \n\n\tCompliance required as indicated prior to January 1, 1976 unless already accomplished. \n\n\tTo provide the required failure warning indication of power loss, accomplish Litton Service Bulletin No. 34-72-80, dated February 20, 1975, or later FAA-approved revision, or an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective December 1, 1975.
2005-12-51: The FAA is adopting a new airworthiness directive (AD) for Rockwell International (Aircraft Specification No. A-2-575 previously held by North American and recently purchased by Boeing) Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, SNJ-7, and T-6G airplanes; and Autair Ltd. (Aircraft Specification No. AR-11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT-16) airplanes. This AD contains the same information as emergency AD 2005-12-51 and publishes the action in the Federal Register. It requires immediate and repetitive inspections of the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of both wings for fatigue cracks; and, if any crack is found, replacement of the cracked angle with a new angle. This AD is the result of a report of a Rockwell International Model SNJ-6 (AT-6F) airplane crash that occurred on May 9, 2005, resulting in two fatalities. We are issuing this AD todetect and correct any fatigue crack in the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of either wing, which could result in failure of the wing. This failure could lead to loss of control of the aircraft.
97-05-11 R1: This amendment revises an existing airworthiness directive (AD), applicable to AlliedSignal Inc. ALF502 and LF507 series turbofan engines, that currently requires initial and repetitive inspections of the oil system chip detectors and oil filter bypass valve, and optional installation of an improved oil filter bypass valve, to ensure the integrity of the reduction gear system and overspeed protection system. This amendment adds an initial inspection threshold for the oil maintenance requirements that was inadvertently omitted from AD 97-05-11, and makes editorial corrections. Paragraphs (b) through (f) of AD 97-05-11 have been rearranged in this AD to make these corrections. This amendment is prompted by the inadvertent omission of the initial inspection threshold. The actions specified by this AD are intended to prevent No. 4 and 5 duplex bearing failure, which can result in a Stage 4 low pressure turbine (LPT) rotor failure, an uncontained engine failure, and damage tothe aircraft.
74-18-04: 74-18-04 BEECH: Amendment 39-1938. Applies to Model A100 (Serial Numbers B-90 through B-92, B-94 through B-102, B-104, B-105, B-107 through B-109, B-111, B-115, B-116, B-118, B-119 and B-121 through B-204) airplanes (except any aircraft serials listed which are equipped with the optional 300 ampere generator system). Compliance: Required as indicated, unless already accomplished. To prevent the fuel transfer sump drain line tube assemblies from contacting the reverse current diode heat sink, accomplish the following: A) Prior to further flight, visually inspect the fuel transfer sump drain line tube assemblies (P/N 100-920001-113 LH and P/N 100-920001-114 RH) for a minimum separation of one-half inch between the fuel transfer sump drain line tube assemblies and the reverse current diode heat sink, located in the aft landing gear wheel wells. Hand form and temporarily support the fuel transfer sump drain line tube assemblies with suitable clamps and/or brackets as necessary to maintain this separation. B) Within 200 hours' time-in-service after the effective date of this AD, remove existing fuel transfer sump drain line tube assemblies (P/N 100-920001-113 LH and P/N 100- 920001-114 RH) and install new fuel transfer sump drain line tube assemblies (P/N 100-920001- 205 LH and P/N 100-920001-206 RH) in accordance with Beech Service Instruction 0668-281 or subsequent revisions. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective August 30, 1974.
87-05-06: 87-05-06 CASA: Amendment 39-5561. Applies to CASA Model C-212 series airplanes listed in CASA Service Bulletin 212-76-04, dated October 23, 1985, certificated in any category. Compliance is required within 11 months after the effective date of this AD. To prevent the partial loss of controllability of the airplane due to an uncontrollable propeller, accomplish the following, unless previously accomplished: A. Modify the propeller feathering control system in accordance with CASA Service Bulletin 212-76-04, dated October 23, 1985. B. 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. C. 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 modification 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 Construcciones 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 becomes effective March 25, 1987.
2005-14-08: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, -200, -300, and 747SP series airplanes. That AD currently requires certain inspections to find missing or alloy-steel taperlock fasteners (bolts) in the diagonal brace underwing fittings, and corrective actions if necessary. For airplanes with missing or alloy-steel fasteners, that AD also mandates replacement of certain fasteners with new fasteners, which constitutes terminating action for certain inspections. This new AD expands the applicability to include additional airplane models and requires a new inspection to determine fastener material and to find missing or broken fasteners, and related investigative/corrective actions if necessary. This AD is prompted by reports indicating that cracked fasteners made of A286 material were found on airplanes that had only fasteners made of A286 material installed in the area common to the diagonal brace underwing fittings.We are issuing this AD to prevent loss of the underwing fitting load path due to missing or damaged alloy-steel or A286 taperlock fasteners, which could result in separation of the engine and strut from the airplane. \n\n\nDATES: This AD becomes effective August 15, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 747-57A2312, Revision 1, dated April 29, 2004, is approved by the Director of the Federal Register as of August 15, 2005. \n\n\tOn August 1, 2001 (66 FR 34094, June 27, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-57A2312, dated June 15, 2000.
75-12-05: 75-12-05 MCCLISH (Funk): Amendment 39-2225: Applies to all McClish (Funk) Model B, B75L, B85C and Funk C Aircraft. 1. Affects wing forward external support struts and rear fuselage lower longerons at the tail post. a. Within the next ten hours' time in service or one month, whichever occurs first, after the effective date of this Airworthiness Directive, unless accomplished within the last 90 hours in service or 11 months, accomplish the following: b. Inspect the wing forward external support struts at the lower end where the aileron cable enters the strut, for corrosion and cracks. c. Inspect the lower fuselage longerons at the tail post and weldments in the rudder hinge post area, for corrosion and cracks. 2. The inspection specified in paragraph (1) must be repeated at intervals not to exceed 100 hours' time in service or 12 months, whichever occurs first. 3. Before further flight, all corroded or cracked parts must be replaced with the same partnumber or with approved equivalent parts, or repaired in accordance with an approved repair procedure. 4. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection time in this Airworthiness Directive. Repairs and equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Substantiating data for repairs and equivalent parts must be submitted by an owner or operator through an FAA Maintenance Inspector. This amendment is effective June 5, 1975.