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91-15-06: 91-15-06 MCDONNELL DOUGLAS: Amendment 39-7069. Docket No. 90-NM-279-AD. \n\n\tApplicability: All Model DC-8F, DC-8-61F, -62F, -63F, -71F, -72F, and -73F series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent inadvertent opening of the forward upper cargo door in flight, a condition which could result in loss of pressurization and reduced controllability of the aircraft, accomplish the following: \n\n\tA.\tWithin four months after the effective date of this AD, and thereafter at intervals not to exceed one year, perform magnetic particle inspections on the cargo door latch spool fitting attach bolts or replace the non-Inconel (H-11) cargo door latch spool fitting attach bolts with new bolts, in accordance with the Accomplishment Instructions for Phase 2 of McDonnell Douglas DC-8 Service Bulletin 52-82 Revision 3, dated October 19, 1990 (hereafter referred to as "the Service Bulletin"). \n\n\t\t1.\tIf a bolt does not pass the magnetic particle inspection, prior to further flight, replace it with a new bolt and seal in accordance with the Service Bulletin. \n\n\t\t2.\tIf a bolt passes the magnetic particle inspection, prior to further flight, reinstall the bolt and seal in accordance with the Service Bulletin. \n\n\tB.\tThe inspections required by paragraph A. of this AD are not required for Inconel bolts, part numbers RA21026-7-23, 77711-7-24, 3D0031-7-24, VCC0098-7-24, 1489-7-24, or 577-7-24. \n\n\tC.\tWithin two years after the effective date of this AD, replace all non-Inconel cargo door latch spool fitting attach bolts with Inconel bolts, part numbers RA21026-7-23, 77711-7-24, 3D0031-7-24, VCC0098-7-24, 1489-7-24, or 577-7-24, in accordance with the Service Bulletin. \n\n\tInstallation of these Inconel bolts constitutes terminating action for the requirements of paragraph A. of this AD. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanesunpressurized to a base for the accomplishment of the requirements of this AD. \n\n\tE.\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, Los Angeles 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, Los Angeles ACO. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HCW (54-60). These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-7069, AD 91-15-06) becomes effective on August 16, 1991.
75-27-05: 75-27-05 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2477. Applies to Alouette helicopter Models SE-3130, SE-313B, SA-3180, SA-318C, SA-315B, SE-3160, SA-316B, SA-319B, and SA-316C incorporating 3130 series main rotor blade(s) with serial number 9554 and lower, and 3160 series main rotor blade(s) with serial number 6999 and lower. Compliance is required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished in accordance with Lama Service Bulletin No. 01.04 for the Model SA- 315B, or Alouette Service Bulletin No. 01.30 for the other designated models. To prevent failure of the main rotor blades due to corrosion, inspect the blade spar in the section between the attachment fitting and root end rib for corrosion, repair as necessary, and return to service, in accordance with paragraphs 2 B(2), 2 B(3), 2 B(4) and 2 C of SGAC- approved Alouette Service Bulletin No. 01.30, as amended August 30, 1972, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region. This amendment becomes effective on January 19, 1976.
71-06-01: 71-06-01 BEECH: Amdt. 39-1170 as amended by Amendment 39-1222 is further amended by Amendment 39-1321. Applies to all 99 series airplanes (Serial Numbers as applicable). Compliance: Required as indicated, unless already accomplished. To preclude the occurrence of faults, failures and improper operation, accomplish the following: A) On all 99 series airplanes (Serial Numbers U-1 through U-95, U-97 through U- 127, U-130 through U-133, U-135 and U-136) within the next 100 hours' time-in-service after the effective date of this AD, modify the flap position selector in accordance with Beechcraft Service Instruction 0328-158 or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. B) On all 99 series airplanes (Serial Numbers U-1 through U-133, U-135 and U- 136) within the next 100 hours' time-in-service after the effective date of this AD, modify the landing gear indicator and warning device in accordance with Beechcraft Service Instruction 0313-158 and 0318-350, or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. C) On all 99 series airplanes (Serial Numbers U-2 through U-103, U-105 through U- 133, U-135 and U-136) within the next 75 hours' time-in-service after the effective date of this AD, modify the gear selector panel in accordance with Beechcraft Service Instructions 0299-395 or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. D) On all 99 series airplanes (Serial Numbers U-1 through U-103 and U-106 through U-135) within the next 75 hours' time-in-service after the effective date of this AD, modify the instrument static air system in accordance with Beechcraft Service Instruction 0291- 394, Rev. 1, or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. E) On Models 99 and 99A (Serial Numbers U-1 through U-136) airplanes within the next 100 hours' time-in-service after the effective date of this AD (March 16, 1971), inspect and test the electrical power distribution system in accordance with Beechcraft Service Instructions 0348-351 or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri. Amendment 39-1170 became effective March 16, 1971. Amendment 39-1222 became effective June 3, 1971. This Amendment 39-1321 becomes effective October 19, 1971.
87-14-02: 87-14-02 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-5732. Applies to IO-520, IO-550, and TSIO-520 series engines with starter adapter shaftgear P/N 649343, a freon compressor, and 25 hours or less time in service installed on the following engines: New Engines Serial Numbers IO-520BB S/N 578239 thru 578250, 578255 thru 578261, 578271, 578272 IO-550B S/N 675329, 675330, 675334 thru 675336 TSIO-520UB S/N 527091, 527093 TSIO-520BE S/N 528383, 528389 IO-520BA S/N 249568 thru 249570, 249588 thru 249593 IO-520BB S/N 248585, 248586, 274505 thru 274520, 274522 thru 274526, 274529, 274532, 274536, 274537, 274540, 274544, 274545, 274549, 274550, 274552, 274554 IO-550B S/N 249124 thru 249130, 249132 Rebuilt Engines Serial Numbers TSIO-520UB S/N 248867, 248869 TSIO-520LB S/N 237242, 237244, 237247, 241909, 241910 TSIO-520WB S/N 274004 thru 274008, 274012 thru 274018 TSIO-520BE S/N 273505 thru 273510 Compliance is required before further flight unless already accomplished. To prevent possible starter adapter shaftgear failure, which could result in loss of lubricating oil and subsequent complete loss of engine power, accomplish the following: (a) Determine if the installed engine(s) has a freon compressor installed. (1) If no freon compressor is installed, no further action is required, proceed to paragraph (f). (b) Engines in compliance with priority letter AD 87-12-12, but not included in the engine serial numbers listed in this AD, may reinstall the air conditioner drive belt. Proceed to paragraph (f). (c) Determine the time in service of the starter adapter shaftgear P/N 649343 for each installed engine. If the time in service is greater than 25 hours with the freon compressor drive belt installed, no further action is required. Proceed to paragraph (f). If the time in service is less than 25 hours, accomplish paragraphs (d) or (e) as applicable. (d) If the engine was new when installed, remove the starter adapter assembly P/N 642087, and return to the manufacturer for replacement. Install the replacement assembly, and proceed to paragraph (f). (e) If the installed engine is a rebuilt engine, gain access to the drive sheave mounted on the rear of the starter adapter shaftgear. Determine, using a light and mirror, if the drive sheave attaching nut is castellated. (1) If the nut is castellated with a cotter key installed, no further action is required, proceed to paragraph (f). (2) If a steel lock nut is installed, inspect the center of the shaft to determine if the shaft has drilled cotter key holes (See TCM Service Bulletin M87-13, dated 29 June 1987, Figure 1). (i) If the shaft has drilled holes, no further action is required, proceed to paragraph (f). (ii) If the shaft is undrilled, remove the starter adapter assembly P/N 642087 and return to the manufacturer for replacement. Install the replacement assembly. (f) Make appropriate logbook entry showing compliance with this AD. NOTES: 1. Contact TCM for shipping instructions. 2. When replacing the starter adapter assembly, retain the drive sheave for reinstallation on new assembly. 3. TCM Service Bulletin M87-13, dated 29 June 1987, refers to this subject. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Federal Aviation Administration, Central Region, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia 30349. Priority letter AD 87-14-02 superseded priority letter AD 87-12-12. This amendment 39-5732 becomes effective October 5, 1987, as to all persons except those persons to whom it was made immediately effective by priority letter AD No. 87-14-02, issued July 8, 1987, which contained this amendment.
2021-07-02: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200 series airplanes. This AD was prompted by reports indicating that the pitot heat switch is not always set to ON, which could result in misleading air data. This AD requires replacement of pitot anti-icing system components, installation of a junction box and wiring provisions, repetitive testing of the anti- icing system, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
96-12-23: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) 150 and A150 series and Models 152 and A152 airplanes that have a Bush Conversions, Inc., Short Takeoff and Landing (STOL) kit incorporated in accordance with Supplemental Type Certificate (STC) SA1371SW. This action requires measuring the wing stall fence for maximum height, and installing a smaller fence if the fence exceeds the maximum height of 1.28 inches. An accident of a Cessna Model 152 airplane where the STOL kit adversely affected the airplane's stall characteristics prompted this action. The actions specified by this AD are intended to prevent the airplane from entering a stall condition because of improper wing stall fence height, which could result in loss of control of the airplane.
96-06-02: This amendment supersedes an existing airworthiness directive (AD), applicable to The Enstrom Helicopter Corporation Model (Enstrom) F-28A, F-28C, 280, and 280C helicopters, that currently requires an initial and repetitive visual inspections of the upper swashplate bearings for corrosion, and replacement of defective upper swashplate bearings with airworthy bearings. This amendment requires that the visual inspections apply to both the upper and lower swashplate bearings (bearings); expands the applicability to include the Model F-28C-2 helicopter; limits the applicability to those affected helicopters manufactured prior to January 1, 1981; establishes a retirement life of 1,200 hours time-in-service for certain bearings; and provides a corrected upper swashplate bearing part number. This amendment is prompted by the necessity to require visual inspections of the lower swashplate bearings; to expand the applicability to include the Model F-28C-2 helicopter; to establish a retirement life for certain bearings; and to correct the upper swashplate bearing part number from the existing AD. The actions specified by this AD are intended to prevent failure of the bearings and subsequent loss of control of the helicopter.
2016-23-05: We are superseding Airworthiness Directive (AD) 2007-25-08 for Eurocopter France (now Airbus Helicopters) Model SA-365N1, AS-365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2007-25-08 required checking the tail rotor gearbox (TGB) oil, inspecting the magnetic plug, and either replacing the TGB or performing additional inspections. This AD was prompted by reports of new occurrences of loss of yaw control due to failure of the control rod bearing. This AD requires checking the TGB oil level and replacing the bearing with a new part-numbered bearing. These actions are intended to detect and prevent damage to the bearing resulting in end play, loss of tail rotor pitch control, and subsequent loss of control of the helicopter.
2016-23-02: We are superseding Airworthiness Directive (AD) 2006-19-12 for certain The Boeing Company Model 777-200 and -300 series airplanes. AD 2006-19-12 required inspecting the lower web of the aft fairing of the engine struts for any discoloration, and doing related investigative and corrective actions if necessary; inspecting the heat shield castings for any damage and doing corrective action if necessary; installing gap cover strips; and replacing insulation blankets with new insulation blankets. This new AD retains those requirements and also requires, depending on airplane configuration, one-time or repetitive detailed inspections for cracking and deformation, as applicable, of the aft fairing lower structure, and one-time or repetitive conductivity inspections of the aft fairing lower structure, and related investigative and corrective actions if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by a report that an aft fairing lower spar web exceeded the allowable conductivity limits. We are issuing this AD to address the unsafe condition on these products.
87-15-04: 87-15-04 HARTZELL PROPELLER, INC.: Amendment 39-5667. Applies to Hartzell Model HC-B4MN-5( ) propellers installed on CASA Model C-212-CC and -CF airplanes. Compliance required at next propeller overhaul or within 30 days after the effective date of this AD, whichever occurs sooner, unless already accomplished. To prevent pitch change rod failure which could result in loss of propeller control, accomplish the following: Replace the spring assembly, P/N B-831-54, with spring assembly, P/N B-831-64, which includes a strengthened pitch change rod in accordance with Hartzell Service Bulletin No. 153, dated May 1, 1987. 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. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Chicago Aircraft Certification Office, may adjust the compliance time specified in this AD. Hartzell Service Bulletin No. 153, dated May 1, 1987, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive which have not already received this document from the manufacturer may obtain copies upon request to Hartzell Propeller, Inc., 1800 Covington Avenue, Piqua, Ohio 45356. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, Attn: Rules Docket No. 87-ANE-20, 12 New England Executive Park, Burlington, Massachusetts 01803 weekdays, except federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment, 39-5667, becomes effective on July 31, 1987.