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79-13-01: 79-13-01 BEECH: Amendment 39-3504. Applies to Models C50, D50, D50A, D50B, D50C, D50E, E50, F50, G50, H50, and J50 airplanes modified in accordance with STC SA76SW certified in all categories. Compliance is required as indicated unless already accomplished. To reduce the possibility of powerplant fire occurrence and improve powerplant fire containment and detection capabilities, accomplish the following: a. Within 25 hours time-in-service after the effective date of this Amendment, incorporate into the existing Airplane Flight Manual, the temporary Airplane Flight Manual Supplement Included in this AD as Figure 1 or Excalibur Aviation Flight Manual Supplement dated May 31, 1979, or later approved revision. b. Within 100 hours time-in-service after the effective date of this Amendment, accomplish items (1), (2), (3), and (4) below, except that this compliance time may be extended to 200 hours time-in-service if the inspection of components forward of the firewall required by AD 79-01-02 is accomplished at intervals no greater than 50 hours time-in-service during this compliance time extension: (1) Replace existing flexible fuel, oil, hydraulic, and fuel or oil vapor carrying hose assemblies except engine breather and drain lines in the engine compartment with equivalent length and diameter hoses having strength and fire resistance qualities meeting FAA Technical Standard Order C53A, Type C or D, or as specified below. Hose assemblies fabricated or Stratoflex Type 111 or 130 hose covered by fire resistant sleeve, Stratoflex Type 2650 or 2607, or Aeroquip hose Type 303 covered with fire resistant sleeve Type AE102 or 624, or an FAA-approved equivalent are acceptable. (Pressure test the hose assemblies in accordance with industry practice.) Use old hoses as a pattern when fabricating new hoses. Caution should be exercised to assure end fittings on new hoses are equivalent to old hose end fittings. Install hoses observing the manufacturer's torque limits. Apply paint or torque putty to fittings after tightening. (2) On airplanes having engines with the Bendix fuel injection system, after changing all engine and installation fuel system hoses but prior to connecting the hose at the fuel injector nozzle located at the top of the induction housing, cap this hose at the nozzle end, select main tanks, turn main boost pumps ON, place mixture controls in rich position, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck prior to installing hose on nozzle fittings. (3) On airplanes other than those specified in paragraph b(2) above, after changing all installation fuel system hoses, with mixture control in "cut off" position, select main tanks, turn main boost pump ON, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck. (4) After determining that no fuel is trapped in the induction system, conduct the run-up specified in Figure 1 and inspect all hoses and fittings for signs of fuel or oil leakage. c. On or before October 19, 1979, install continuous type fire detector systems in the engine compartment and wheel wells in accordance with the Beech Service Kit No. 80-9010, or the Shadin Kit No. 2125-1, with revisions as covered by Excalibur Aviation Company Service Bulletin No. 79-01. d. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. Beechcraft Service Instructions No. 0999, Shadin Report No. 2125, and Excalibur Aviation Company Service Bulletin 79-01 or later approved revisions referenced herein cover the subject matter of this AD. This amendment becomes effective July 5, 1979. FIGURE 1 TEMPORARY AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH MODEL 50 SERIES AIRPLANES (AD 79-13-01 requires this supplement to remain in the airplane flight manual until replaced by Excalibur Aviation Company Flight Manual Supplement dated May 31, 1979, or later approved revisions.) Model N- S/N In addition to the presently specified preflight procedures, prior to first flight of each day, accomplish the following: 1. Start both engines and operate at 1500 RPM. After the oil pressures stabilize, shut down the engines using the mixture control. 2. Open the cowl doors on both sides of the engines and check all engine compartment fluid hoses and fittings for indications of fluid (fuel or oil) leakage. Check the wheel wells for these same conditions using a flashlight or supplemental light as necessary to provide adequate illumination of the area. 3. Correct any leak detected and secure cowl doors. 4. Record in Airplane Maintenance Records.
91-24-01: 91-24-01 GENERAL ELECTRIC COMPANY: Amendment 39-8086. Docket No. 91-ANE-43. Supersedes AD 90-24-12, Amendment 39-6808. Applicability: General Electric Company (GE) CF6-6 series turbofan engines installed on but not limited to McDonnell-Douglas DC-10 aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent rupture of the compressor rear frame (CRF) casing that could result in an engine shutdown, aircraft damage, and aborted takeoff, accomplish the following: (a) At the next scheduled open cowl check, but not later than 100 cycles in service (CIS) after the effective date of this AD, inspect the CRF outer case compressor discharge pressure (CDP) manifold port plug weld area for cracks in accordance with GE CF6-6 Service Bulletin (SB) 72-971, Revision 2, dated August 27, 1991. (b) Remove from service, prior to further flight, CRF casings which exceed the serviceable limits specified in Table 1 or Table 2, as applicable, of GE CF6-6 SB 72-971, Revision 2, dated August 27, 1991. (c) For engines with CRF casings inspected after December 11, 1990 (the effective date of AD 90-24-12), reinspect and remove from service CRF casings in accordance with the inspection intervals and crack limits specified in Table 1 of GE CF6-6 SB 72-971, dated October 2, 1990, until the first scheduled inspection after the effective date of this AD. (d) Thereafter, reinspect and remove from service CRF casings in accordance with the inspection intervals and crack limits specified in Table 1 or Table 2, as applicable, of GE CF6-6 SB 72-971, Revision 2, dated August 27, 1991. (e) At the next shop visit, but not later than 4,500 CIS after the effective date of this AD, perform a visual, fluorescent-penetrant, and radiographic inspection of the CRF, and rework the CRF in accordance with GE CF6-6 SB 72-977, dated March 15, 1991. (f) For the purpose of this AD, a shop visit is defined as the CRF exposed at the piece-part level. (g) Compliance with paragraph (e) of this AD eliminates the inspection requirements of paragraphs (a), (b), (c), and (d) of this AD and constitutes a terminating action to this AD. (h) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Engine Certification Office. (i) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (j) The reinspections and removal of CRF casings shall be done in accordance with General Electric CF6-6 Service Bulletin 72-971, dated October 2, 1990. This incorporation by reference was previously approved by the Director of the Federal Register at 55 FR 48591, (December 11, 1990) in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies of General Electric service bulletins may be obtained from General Electric Aircraft Engines, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. (k) The inspections and rework shall be done in accordance with the following General Electric Company documents: Document Number Page Number Issue/Rev Date GE CF6-6 SB 72-971 1-11 Revision 2 8/27/91 12 Original 10/2/90 Total: 12 pages GE CF6-6 SB 72-977 1-34 Original 3/15/91 Total: 34 pages This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies of General Electric service bulletins may be obtained from General Electric Aircraft Engines, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. (l) This amendment becomes effective on May 26, 1992.
2013-05-15: We are adopting a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44 and R44 II helicopters equipped with emergency floats. This AD requires replacing the inflation valve assembly. This AD was prompted by the failure of the emergency floats to deploy during a factory test because a needle was binding within the inflation valve assembly. The actions are intended to prevent the failure of the floats to inflate during an emergency landing.
98-21-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB 2000 series airplanes. This action requires repetitive functional tests (checks) to verify proper operation of the nose wheel steering system (NWSS) limitswitch, and replacement of the existing limitswitch with a new limitswitch, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent combined failure of the limitswitch and the feedback shaft in the NWSS servo unit, which could result in uncommanded nose wheel steering deflection and reduced controllability of the airplane on the ground during takeoff or landing.
80-12-05 R2: 80-12-05 R2 BRITISH AEROSPACE, INC. (formerly Hawker Siddeley Aviation, Ltd.): Amendment 39-3789 as amended by Amendment 39-4390 is further amended by Amendment 39- 4580. Applies to Models HS/DH/BH 125 airplanes, all series, certificated in all categories. Compliance is required as indicated. To detect and correct cracks in the bridge casting of the nose landing gear drag stay assembly and prevent possible nose landing gear collapse, accomplish the following: (a) Upon the accumulation of 2000 landings on the bridge casting or within the next 100 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 900 landings on the bridge casting from the last inspection or every two years, whichever occurs first, inspect and rework or replace as necessary the bridge casting P/N 25UN49A in accordance with Section 2A "Accomplishment Instructions" of British Aerospace Service Bulletin 32-184, Revision 2, dated October 20, 1980, or an FAA-approved equivalent. (b) Prior to the installation of modified bridge casting P/N 25UN49AD held as spares or in store, accomplish the inspection and rework specified in paragraph (a) of this AD. NOTE: British Aerospace Modification 252677 introduces a new production standard of bridge casting P/N 25UN49AD, which incorporates "radiusing," polishing, and special surface treatment of the bridge area. (c) For modified bridge castings, P/N 25UN49AD, continue to inspect in accordance with paragraph 2.A., "Accomplishment Instructions," of British Aerospace Service Bulletin 32- 184, Revision 3, dated June 24, 1982, or an FAA-approved equivalent. (d) For purposes of complying with this AD, for airplanes for which no records exist that indicate the number of landings the bridge casting has accumulated, the number of landings may be estimated by using the total airplane time in service in hours on a 1-to-1 ratio. (e) Upon request of the operator, an FAA maintenance inspector 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 increased inspection interval requested for that operator. (f) 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. 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). Amendment 39-3789 became effective June 16, 1980. Amendment 39-4390 became effective June 8, 1982. This Amendment 39-4580 becomes effective March 16, 1983.
2006-12-08: The FAA is adopting a new airworthiness directive (AD) for Goodrich evacuation systems approved under TSO-C69b and installed on certain Airbus Model A330-200 and -300 series airplanes, Model A340-200 and -300 series airplanes, and Model A340-541 and -642 airplanes. This AD requires inspecting to determine the part number of the pressure relief valves on the affected Goodrich evacuation systems, and corrective action if necessary. This AD results from a report indicating that, during maintenance testing, the pressure relief valves on the affected Goodrich evacuation systems did not seal when activated, which caused the pressure in the escape slide/raft to drop below the minimum allowable raft mode pressure. We are issuing this AD to prevent loss of pressure in the escape slides/rafts after an emergency evacuation, which could result in inadequate buoyancy to support the raft's passenger capacity during ditching, and increase the chance for injury to raft passengers.
2013-05-21: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC130 B4 helicopters with a cabin vibration damper installed. This AD requires installing a vibration damper casing assembly on both sides of the helicopter. This AD was prompted by a crack and failure of a cabin vibration damper blade. The actions of this AD are intended to modify the cabin vibration damper assembly to prevent contact with the flight controls in the event of a cabin vibration blade failure, jamming of a flight control, and subsequent loss of control of the helicopter.
98-20-37: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and -300 series airplanes, that requires the replacement of certain switches located in the cabin attendant's panel at doors 1 and 3 right with new, improved switches. This amendment is prompted by reports indicating that fires have occurred on some airplanes due to the internal failure of some of these switches. The actions specified by this AD are intended to prevent the installation and use of such switches that could short circuit when they fail, and consequently cause fire and smoke aboard the airplane.
91-18-10: 91-18-10 BOEING: Amendment 39-8013. Docket No. 90-NM-206-AD. \n\n\tApplicability: Model 767 series airplanes equipped with brake part numbers (P/N) identified in paragraph (a) of this AD, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of main landing gear braking effectiveness, accomplish the following: \n\n\t(a)\tWithin 180 days after the effective date of this AD, incorporate the maximum brake wear limits, shown below, into the FAA-approved maintenance inspection program. \n\nBrake Mfr. \tBrake P/N\t Boeing P/N\t Max. Wear Limit \n\nBendix\t\n2607092-1\t\nS160T200-12\t\n2.15 inches \nBendix\t\n2607092-2\nS160T200-13\n2.15 inches \nBendix\t\n2607092-3\t\nS160T200-14\n2.15 inches \nBendix\t\n2607092-4\nS160T200-15\n2.15 inches \nBendix\t\n2608812-4\t\nS160T300-12\n2.56 inches \nBendix\t\n2608812-6\t\nS160T300-14\n2.90 inches \n\t\n\t(b)\tAn alternative method 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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\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\tThis amendment (39-8013, AD 91-18-10) becomes effective on November 12, 1991.
90-05-10: 90-05-10 SAAB-SCANIA: Amendment 39-6530. Docket No. 90-NM-19-AD. Applicability: Model SF-340A series airplanes, Serial Numbers 004 through 159; and SAAB 340B series airplanes, Serial Numbers 160 through 166; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the loss of structural integrity of the powerplant installation, accomplish the following: A. Within 50 hours time-in-service after the effective date of this AD, inspect the drag strut bolts, lower fittings, and attaching bolts to verify the type of nuts/collars installed, in accordance with SAAB Service Bulletin 340-54-026, dated December 1, 1989. 1. If the inboard and outboard lower drag strut support fittings have been installed with Hi-Lock pins and MS nuts, Part No. MS21042L3, no further action is required. 2. If the inboard and outboard lower drag strut support fittings have not been installed with MS21042L3 nuts, prior to further flight, accomplish the following: a. Remove the seven collars at the lower drag strut support fitting, in accordance with Figure 1 of the service bulletin. b. Perform a visual inspection for defects around the hole edges. If defects are found, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. c. Install MS21042L3 nuts, and AN960KD10 or AN960KD10L washers, in accordance with paragraph 2.B.(4) of the service bulletin. 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. 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. C. Special flight permits may be issuedin 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 information from the manufacturer may obtain copies upon request to SAAB-Scania, Product Support, S- 581.88, Linkoping, Sweden. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6530, AD 90-05-10) becomes effective on March 21, 1990.
2013-05-17: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-61A, D, E, L, N, NM, R, and V helicopters to require replacing each forward and aft fuel system 40 micron fuel filter element with a 10 micron nominal (40 micron absolute) fuel filter element. This AD was prompted by a National Transportation Safety Board (NTSB) review of in-service events where engine performance degradation occurred, and the review determined that some of these events were caused by contaminants larger than 10 microns present in the engine fuel control units (FCUs). The actions are intended to prevent particulate contamination in the FCU, which could lead to malfunction of an internal valve, power loss at a critical phase of flight, and loss of control of the helicopter.
96-12-03 R2: This amendment revises Airworthiness Directive (AD) 96-12-03 R1, which applies to Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B airplanes that are equipped with aft lower fuselage wing attach fittings incorporating part number (P/N) 76090, P/N 2-2107-1, or P/N 1-210-102. AD 96-12-03 R1 currently requires repetitively inspecting the aft lower fuselage wing attach fitting on both wings for cracks, and modifying any cracked aft lower fuselage wing attach fitting. Modifying both aft lower fuselage wing attach fittings eliminates the repetitive inspection requirement of AD 96-12-03. Aviat started incorporating modified aft lower fuselage wing attach fittings on newly manufactured airplanes beginning with serial number 5337, instead of 5349 as referenced in the existing AD. This AD retains the repetitive inspection and possible modification requirements of AD 96-12-03 R1, and will change the applicability accordingly. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked fuselage wing attach fitting.
60-20-04: 60-20-04 LOCKHEED: Amdt. 203 Part 507 Federal Register September 28, 1960. Applies to 188 Aircraft Serial Numbers 1002, 1004 Through 1102, 1104 Through 1126, and 2001 Through 2015. Compliance required by the next 300 hours' time in service after October 28, 1960. Leaking lavatory tank ground drain valves have permitted drainage to the exterior surface of the aircraft in flight, resulting in ice formation which came off and struck the stabilizer. Since such ice formation is hazardous to aircraft in flight and to persons on the ground, all lavatory tank ground drain valves must be modified to incorporate LAC seal No. 838228-1 or equivalent. (LAC 88/SB-407 covers the intent of this change.) This directive effective October 28, 1960.
88-25-09: 88-25-09 AEROSPATIALE (SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE): Amendment 39-6237. Final copy of priority letter AD. (Docket No. 88- ASW-59) Applicability: All Aerospatiale Model AS 355 series helicopters containing Part Number (P/N) 355A34-1037-00, tail rotor drive shaft, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent tail rotor drive shaft failure, which could result in the loss of control, accomplish the following: (a) Within the next 50 hours' time in service after receipt of this AD, and thereafter at intervals not to exceed 100 hours' time in service, perform the vibration level measurement with the aircraft on the ground and with the rotor turning, in accordance with Maintenance Work Card 65-10-00-604. (1) If the measured vibration level is equal to or above 3 inches per second (IPS)-- (i) Replace the tail rotor drive shaft with a serviceable part prior to further flight; or(ii) The tail rotor drive shaft may be operated for no more than an additional 50 hours' time in service provided the vibration level is reduced to 1.75 IPS or below, and no cracks are found by the following inspections. Before the next flight and thereafter at intervals not to exceed 10 hours' time in service, inspect the inside surface of the shaft in the area of the forward flange and splined fitting attachment (both ends of the shaft, adjacent to the Jo- bolts) for cracks. If cracks are found, replace the tail rotor drive shaft with an airworthy shaft prior to further flight. (2) If the measured vibration level is above 1.75 IPS, but less than 3 IPS: (i) Clean the fan assembly in accordance with Maintenance Work Card 12-00-00-306. (ii) Perform a new vibration level check. (iii) If the vibration level is less than 1.75 IPS after cleaning, no further action is required. (iv) If the vibration level is above 1.75 IPS, balance the fan assemblyin accordance with Maintenance Work Card 65-10-00-604, and perform a new vibration level check. (A) If the vibration level is less then 1.75 IPS after balancing, no further action is required. (B) If the measured vibration level measures above 1.75 IPS, inspect the sliding flange splines for wear and the fan bearings for abnormal play in accordance with the applicable Maintenance Work Cards. Replace parts found outside specified limits and perform a new vibration check. If the vibration level remains above 1.75 IPS, replace the tail rotor drive shaft with a serviceable part prior to further flight. (3) If the measured vibration level is below 1.75 IPS, no further action is required. (b) Accomplish the vibration level measurement and shaft replacement, as necessary, in accordance with the instruction of paragraph (a) before and after the replacement of any fan assembly component or any tail rotor drive shaft. (c) Replace the tail rotor drive shaft in accordance with the instructions of paragraph (a)(1) if-- (1) The vibration level exceeded 3 IPS as measured during previous compliance with Aerospatiale Service Bulletin 05.20, before issuance of this AD; or (2) The tail rotor drive shaft was installed when the oil cooler fan was changed for foreign object damage or when the fan bearings were changed for bearing discrepancies. (d) An alternate method of compliance with the AD which provides an equivalent level of safety may be used if approved by the Manager, Rotorcraft Standards Staff, ASW-110, FAA, Fort Worth, Texas 76193-0110. This amendment (39-6237, AD 88-25-09) becomes effective on July 14, 1989, as to all persons except those persons to whom it was made immediately effective by priority letter AD No. 88-25-09, issued December 9, 1988, which contained this amendment.
2013-05-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports of in-service events related to electrical power system malfunctions resulting in damage to electrical load management system (ELMS) P200 and P300 power panels and the surrounding area. This AD requires installing enclosure trays to contain debris in certain ELMS panels, and replacing certain ELMS contactors. We are issuing this AD to prevent contactor failures, which could result in uncontained hot debris flow due to ELMS contactor breakdown, consequent smoke and heat damage to airplane structure and equipment during ground operations, and possible injuries to passengers and crew.
98-20-40: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-100, -200, -300, SP, and SR series airplanes, that requires the installation of shielding and separation of the electrical wiring of the fuel quantity indication system (FQIS). This amendment is prompted by a failure analysis of the FQIS, and by testing results, which revealed that excessive energy levels in the electrical wiring and probes of the fuel system could be induced by electrical transients. The actions specified by this AD are intended to prevent electrical transients, induced by electromagnetic interference (EMI), or electrical short circuit conditions from causing arcing of the FQIS electrical wiring or probes in the fuel tank(s). Such arcing could result in ignition of the fuel tank(s).
89-01-01: 89-01-01 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-6052. Applicability: All SNIAS Model AS 355E, AS 355F, and AS 355F1 helicopters (serial numbers before 5362) fitted with debris guards, Part Numbers (P/N) 355A58-0519-0201 and 355A58-0519-0391, certificated in any category, except those helicopters previously equipped with this identical modification. (Docket No. 87-ASW-62) Compliance: Required within the next 200 hours' time in service, unless already accomplished. To prevent engine failure (flameout) resulting from ingestion of atmospheric moisture in engine inlets, accomplish the following: (a) Install an engine automatic relight system in accordance with SNIAS Service Bulletin AS 355 No. 80.02, Revision 2, approved July 8, 1987 (SB No. 80.02 corresponds to SNIAS Modification AMS 350A07-1823, IFR-VFR versions; AMS 350A07-1856, IFR versions; AMS 350A07-1905, IFR-VFR versions; AMS 350A07-1910, IFR-VFR versions; AMS 350A07- 1920, IFR-VFR version). Installation of the SNIAS relighting kit requires exclusive utilization of Champion or Auburn igniter P/N 6877518 or Champion igniter P/N 23006266 and limits the service life of each newly installed igniter to 1,200 hours' time in service. Any of the required Champion or Auburn igniters already installed and having 1,000 or more hours' time in service must be replaced with new Champion or Auburn P/N 6877518 igniters or Champion P/N 23006266 igniters. NOTE: SNIAS Service Bulletin AS 355 No. 01.18, Revision 2, approved October 5, 1987, also pertains to this engine automatic relight system installation. (b) Incorporate into the applicable RFM the basic flight manual revisions and instrument flight rules (IFR) flight manual supplements (if IFR equipped), or later FAA-approved flight manual revisions, as follows: (1) For the Model AS 355E, basic rotorcraft flight manual, Revision 4, Code Date 87-10. (2) For the Model AS 355F, basic rotorcraft flight manual, Revision 3, Code Date 87-10 and IFR rotorcraft flight manual supplement 11.4, Revision 3, Code Date 87-12. (3) For the Model AS 355F1, basic rotorcraft flight manual, Revision 2, Code Date 87-10, and IFR rotorcraft flight manual supplement 11.4, Revision 1, Code Date 87- 12. (c) To insure that the limited service life of the igniters defined in paragraph (a) above is properly identified and adhered to, the following updates (or future revisions thereto) must be incorporated in the Master Servicing Recommendations-Chapter 5-99 (Airworthiness Limitations): (1) AS 355E, Revision 15, Page 21. (2) AS 355F, Revision 15, Page 23. (3) AS 355F1, Revision 15, Page 23. (d) Upon accomplishing the requirements of paragraphs (a), (b), and (c) above, the placard required by paragraph (a) of AD 86-24-02 may be removed. (e) Upon request, an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Standards Staff, ASW-110, FAA, Fort Worth, Texas 76193-0110. (f) Continuous ignition systems previously found to be equivalent methods of compliance with priority letter AD 86-24-02, dated November 21, 1986; or with Amdt. 39-5796 (52 FR 46985; December 11, 1987) effective January 27, 1988, are approved as equivalent methods of compliance to this AD. The procedure shall be done in accordance with SNIAS Service Bulletin AS 355 No. 80.02, Revision 2, approved July 8, 1987. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1) and 1 CFR Part 51. Copies may be obtained from Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C.This amendment supersedes AD 86-24-02, Amendment 39-5796, which was effective January 27, 1988. This amendment (39-6052, AD 89-01-01) becomes effective January 28, 1989.
89-24-03: 89-24-03 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-6386. Correction issued on May 8, 1990. Docket No. 89-ANE-19. Applicability: TCM Model TSIO-520-UB engines, serial numbers 515000 thru 515999 and 527000 thru 527070, and to all remanufactured and overhauled engines of this model, regardless of serial number, which are equipped with part number (P/N) 642668 turbocharger inlet assembly. Compliance: Required at the next 100 hour inspection or annual inspection, or within 100 flight hours, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 100 flight hours. To prevent possible cracking of the turbocharger inlet assembly which could result in engine compartment fire, accomplish the following: (a) Visually inspect turbocharger inlet assembly P/N 642668 for cracks especially in the weld joints just above the turbine inlet temperature boss. If a crack is found, replace P/N 642668 with P/N 646795 turbocharger inlet assembly, prior to further flight. (b) Make appropriate log book entry showing compliance with this AD. NOTES: (1) Beechcraft Aircraft Corporation Service Communique No. 70, dated October 28, 1983, refers to this subject. NOTES: (2) When determining the P/N assembly installed in order to comply with this AD, a distinguishing feature of the P/N 646795 turbocharger inlet assembly is 2 ribs (approximately 0.25 inches in height, 0.1 inches in width, and 2.1 inches in length) on the top of the turbocharger mating flange. NOTES: (3) If P/N 642668 is not installed, no action is required. (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 submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager,Atlanta Aircraft Certification Office, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. This amendment 39-6386 (AD 89-24-03) became effective on December 4, 1989. This correction becomes effective on June 18, 1990.
98-20-38: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) 200 series airplanes. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD was prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2022-09-11: The FAA is superseding Airworthiness Directive (AD) 2021-14- 17, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2021-14-17 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2021-14- 17, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require the revision of the existing maintenance/inspection program, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
81-05-03: 81-05-03 THE BALLOON WORKS: Amendment 39-4053. Applies to Firefly Models 5, 6, 6B, 7, 7B and 8-24 series hot air balloons equipped with Fire 2 auxiliary heaters incorporating The Balloon Works fuel tanks part numbers BW 3229-A through BW 3229-N and BW 3307-A through BW 3307-H, certificated in all categories. Compliance required within the next 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent inadvertent operation of the Fire 2 heater system during a hard landing, even though the tank valve has been closed, accomplish the following: Modify the Fire 2 fuel tank shut-off valve in accordance with The Balloon Works Service Bulletin B12 dated December 15, 1980, or later FAA approved revision, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southern Region. Make an appropriate maintenance record showing compliance with this AD. This amendment becomes effective March 11, 1981.
75-06-08: 75-06-08 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2124. Applies to G-1159 airplanes certificated in all categories. Compliance required within the next 150 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible loss of all DC and AC power, connect the battery switch ground leads to separate studs at the center overhead panel in accordance with Grumman ASC 188 or in an equivalent manner approved by Chief, Engineering and Manufacturing Branch, Southern Region, Atlanta, Georgia. This amendment becomes effective March 18, 1975.
2022-09-15: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. This AD was prompted by brake system failures during landing due to a brake servo-valve failure resulting from application of an inappropriate oil type during production and maintenance. This AD requires relocating affected servo-valves and revising the existing airplane flight manual (AFM) to provide temporary information necessary to operate airplanes fitted with at least one affected brake servo-valve, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits or prohibits the installation of affected brake servo-valves. The FAA is issuing this AD to address the unsafe condition on these products.
98-20-32: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires an initial cleaning and visual inspection of the distance piece and adjacent side plates of the fuselage wing strut pick-up of the left- and right-stub wings to detect corrosion; rework or replacement of damaged components; and, for certain conditions, follow-on repetitive cleaning and visual inspections of reworked components. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct corrosion of the distance piece and adjacent side plates, which could result in reduced strength of the wing strut attachment to the stub wing on the fuselage, and consequent reduced structural integrity of the main wing.
98-20-33: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) Model T210R airplanes. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD was prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.