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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.