Results
84-13-06 R2: 84-13-06 R2 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA S.p.A.: Priority letter AD 84-13-06 as amended by Amendment 39-5043 is further amended by Amendment 39- 5682. Applies to Model A109A and A109A II series helicopters certificated in any category and equipped with P/N 109-0132-02-11 or -15 tail rotor blades. Compliance is required as indicated unless already accomplished. To prevent possible hazards in flight associated with cracking of the tail rotor blade grip, accomplish the following: (a) Within the next 10 hours time in service, inspect the tail rotor blade grip in accordance with Part I of Agusta Service Bulletin (SB) 109-51, Revision A, or an FAA-approved equivalent, and at each additional 25 hours time in service, accomplish the inspection of Part III of Agusta SB 109-51, Revision A, or an FAA-approved equivalent. (b) Prior to the first flight of each day, comply with Part II of the accomplishment instructions of Agusta SB 109-51, Revision A, or an FAA-approved equivalent. This accomplishment may be conducted by the pilot. (c) Remove from service any tail rotor blade where cracking is found and replace with a serviceable part prior to next flight. (d) An equivalent method of compliance with this AD may be used when approved by the Manager, Brussels Aircraft Certification Office. Priority letter AD 84-13-06 was effective June 29, 1984. Amendment 39-5043 was effective May 13, 1985. This amendment, 39-5682, becomes effective August 30, 1987.
2004-26-10: The FAA is superseding an existing airworthiness directive (AD) for certain RRD Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15, Tay 650-15/10, and Tay 651-54 turbofan engines with ice-impact panels installed in the low pressure (LP) compressor case. That AD currently requires visually inspecting all ice-impact panels and fillers in the LP compressor case for certain conditions, and if necessary, replacing any ice-impact panels and fillers that have those conditions. This AD requires initial and repetitive visual inspections of all ice-impact panels and fillers in the LP compressor case for certain conditions and replacing as necessary, any or all panels. This AD also introduces a new compliance date of no later than March 1, 2005, to have all but one engine on each airplane in compliance with the polysulfide bonding of panels. This AD results from RRD issuing two service bulletins since AD 2004-05-22 was published, that required repetitive visual inspections of panels, and defines a minimum configuration and repair standard. We are issuing this AD to prevent release of ice-impact panels due to improper bonding that can result in loss of thrust in both engines.
2023-13-01: The FAA is superseding Airworthiness Directive (AD) 2008-23- 01, which applies to certain Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2008-23-01 required inspecting to determine the part number and serial number of the fuel tank boost pumps and, for airplanes with affected pumps, revising the operator's airplane flight manual (AFM) and FAA-approved maintenance program. AD 2008-23-01 also required modifying or replacing certain fuel tank boost pumps, which terminated the AFM limitations and the maintenance program revisions. Since the FAA issued AD 2008-23-01, it has been determined that airplanes fitted with a different fuel pump can be subject to cavitation erosion on the wiring conduit. This AD requires inspecting affected fuel pumps for discrepancies and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA). This AD also requires replacing certain other fuel pumps. This AD also limits the installation of affected fuel pumps under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2000-10-20: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that requires repetitive inspections to detect cracking of the fuselage skin in the areas of the left- and right-hand stringerless sidewall window belts, and repair, if necessary. This amendment is prompted by reports of fatigue cracks found in the fuselage skin where the skin thickness steps from 0.40 to 0.23 inch. The actions specified by this AD are intended to detect and correct cracking of the fuselage skin, which could result in reduced structural integrity of the airplane.
2016-15-01R1: The FAA is removing Airworthiness Directive (AD) 2016-15-01, which applied to all Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. AD 2016-15-01 required an inspection to determine trimmable horizontal stabilizer actuator (THSA) part numbers, serial numbers, and flight cycles on certain THSAs; and repetitive replacement of certain THSAs. The FAA issued AD 2016-15-01 to prevent loss of THSA no-back brake (NBB) efficiency. Since the FAA issued AD 2016-15-01, the FAA has issued AD 2022-25-12 to terminate AD 2016-15-01 for Model A310 series airplanes and AD 2023-11-02 to terminate AD 2016-15-01 for Model A300-600 series airplanes. The FAA has also determined that the inclusion of the Model A300 series airplanes in the applicability of AD 2016-15-01 was an inadvertent error. Accordingly, AD 2016-15-01 is removed.
83-02-06: 83-02-06 CASA: Amendment 39-4547. Applies to all CASA 212 series airplanes certificated in all categories. Compliance required within the next 300 hours time in service or 60 days after the effective date of this AD, whichever occurs first. To prevent fuel line blockage accomplish the following unless already accomplished: 1. Modify the ejector fuel filter system in accordance with CASA Service Bulletin 212-28-19 dated December 14, 1982. 2. 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. 3. 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 inspections and/or modifications required by this AD. This amendment becomes effective February 7, 1983.
2023-12-13: The FAA is superseding Airworthiness Directive (AD) 2022-05- 04, which applied to all The Boeing Company Model 737-100, -200, -200C, -300, -400, -500, -600, -700, -700C, -800, -900, and -900ER series airplanes, except for Model 737-200 and -200C series airplanes equipped with a certain flight control system. AD 2022-05-04 required revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate specific operating procedures for instrument landing system (ILS) approaches, speedbrake deployment, go-arounds, and missed approaches, when in the presence of interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band) as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2022-05-04, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band base stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7- 3.98 GHz. This AD requires revising the limitations and operating procedures sections of the existing AFM to incorporate specific operating procedures for ILS approaches, speedbrake deployment, go- arounds, and missed approaches, due to the presence of 5G C-Band interference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-25-02: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A320 series airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in certain areas of the fuselage, and corrective action if necessary. That AD also provides for an optional terminating action for the repetitive inspections. This new AD reduces the compliance threshold and repetitive intervals for the inspections required by the existing AD. This AD is prompted by a full-scale fatigue survey on the Model A320 fleet. We are issuing this AD to detect and correct fatigue cracking of the fuselage, which could result in reduced structural integrity of the airplane. \n\nDATES: This AD becomes effective February 10, 2005. \n\n\tThe incorporation by reference of Airbus Service Bulletin A320-53- 1032, Revision 02, dated December 5, 2001, as listed in the AD, is approved by the Director of the Federal Register as of February 10, 2005. \n\n\tOn February 12, 1999 (64 FR 1114, January 8, 1999), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998.
2023-12-15: The FAA is superseding Airworthiness Directive (AD) 2022-09- 18, which applied to all The Boeing Company Model 707, 717, and 727 airplanes; Model DC-8, DC-9, and DC-10 airplanes; Model MD-10 and MD-11 airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC- 9-87 (MD-87), and MD-88 airplanes; and Model MD 90-30 airplanes. AD 2022-09-18 required revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate specific operating procedures for, depending on the airplane model, instrument landing system (ILS) approaches, non-precision approaches, ground spoiler deployment, and go-around and missed approaches, when in the presence of interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band) as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2022-09-18, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7-3.98 GHz. This AD requires revising the limitations and operating procedures sections of the AFM to incorporate specific operating procedures for, depending on the airplane model, ILS approaches, non-precision approaches, ground spoiler deployment, and go-around and missed approaches, due to the presence of 5G C-Band interference. The FAA is issuing this AD to address the unsafe condition on these products.
86-18-07: 86-18-07 SAAB-FAIRCHILD: Amendment 39-5387. Applies to Model SF-340A airplanes listed in SAAB-Fairchild Service Bulletin SF-340-76-007, Revision 3, dated August 14, 1985, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To prevent engine control cable freezing, accomplish the following: A. Modify the engine control cable system in accordance with SAAB-Fairchild Service Bulletin SF340-76-007, Revision 3, dated August 14, 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 inspections and/or modifications 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 SAAB-Fairchild, Product Support, S-58188, Linkoping, Sweden. 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 September 11, 1986.
2023-12-14: The FAA is superseding Airworthiness Directive (AD) 2022-06- 16, which applied to all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, and 747-400F series airplanes. AD 2022-06-16 required revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate specific operating procedures for takeoff, instrument landing system (ILS) approaches, non-precision approaches, and go around and missed approaches, when in the presence of interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band) interference as identified by Notices to Air Missions (NOTAMs). Since the FAA issued AD 2022-06-16, the FAA determined that additional limitations are needed due to the continued deployment of new 5G C-Band stations whose signals are expected to cover most of the contiguous United States at transmission frequencies between 3.7-3.98 GHz. This AD requires revising the limitations section of the existing AFM to incorporate limitations requiring specific operating procedures, and retains the operating procedures for takeoff, ILS approaches, non-precision approaches, and go-around and missed approaches from AD 2022-06-16, due to the presence of 5G C-Band interference. The FAA is issuing this AD to address the unsafe condition on these products.
81-14-09: 81-14-09 ROCKWELL INTERNATIONAL: Amendment 39-4157. Applies to Models NA-265-40, Serial Numbers 282-1 through 282-97, and NA-265-60, Serial Numbers 306-1 through 306-63, airplanes certificated in any category not modified in accordance with life extension modifications per North American Rockwell Drawing No. 306-053010. COMPLIANCE: Required as indicated unless already accomplished. To prevent inadvertent cabin depressurization, accomplish the following: A) On aircraft with 2,000 or more hours total time-in-service as of the effective date of this AD, within the next 600 hours additional time-in-service or within the next 12 months, whichever occurs first: 1. Conduct a dye penetrant inspection of the door stop (beam) in accordance with the Inspection Instructions of Sabreliner Service Bulletin No. 55 dated March 31, 1980, as revised June 16, 1980. 2. If no cracks are detected, repeat the inspection at intervals not to exceed 600 hours time-in-service or 1year, whichever occurs first. 3. If cracks are detected, replace the cracked part with a new part and after an additional 2,000 hours aircraft time-in-service, resume inspections at 600 hour time-in-service intervals, or modify the aircraft in accordance with Sabreliner Service Bulletin No. 3, dated December 19, 1975, as revised August 4, 1978. Installation of the applicable kit in accordance with Sabreliner Service Bulletin No. 3 eliminates the inspection requirement of this AD. B) On aircraft with less than 2,000 hours total time-in-service as of the effective date of this AD, prior to accumulating 2,600 hours time-in-service or within the next 12 months from the time the aircraft has accumulated 2,000 hours time-in-service, whichever occurs first, accomplish the inspection and corrective action specified in Paragraph A) as applicable. C) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. D) Any equivalent methodof compliance with this AD must be approved by the Chief, Aircraft Certification Program, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 942-4285. E) Record compliance with this AD by an appropriate entry in the airplane maintenance records. This should include those airplanes where the provisions of this AD have already been accomplished. This Amendment becomes effective July 13, 1981.
2004-26-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes equipped with certain forward and aft passenger door emergency escape slides. This AD requires modifying the forward and aft door slides. This AD is prompted by manufacturer testing that has shown contact between the inflation hose and fabric roll, within a short period of time after inflation of the emergency escape slides, can rupture the inflation hose at its end fittings. We are issuing this AD to prevent interference between the inflation hose and slide fabric and rupture of the inflation hose, which could result in incomplete inflation of the emergency escape slides and consequent unavailability of those slides during an emergency evacuation.
2023-11-12: The FAA is adopting a new airworthiness directive (AD) for certain DAHER AEROSPACE (type certificate previously held by SOCATA) Model TBM 700 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as interference between the emergency exit trim panel and the upholstery panel, which could result in additional effort required to open the emergency exit door. This AD requires modification of the gripping strap, which maintains the upholstery panel on the emergency exit trim panel. The FAA is issuing this AD to address the unsafe condition on these products.
86-19-06: 86-19-06 BOEING: Amendment 39-5404. Applies to Boeing Model 737-300 airplanes listed in Boeing Service Bulletin 737-21-1085, dated February 14, 1986, certificated in any category. Compliance required within 180 days after the effective date of this amendment, unless already accomplished. \n\n\tTo ensure air ducts have adequate flammability characteristics accomplish the following: \n\n\tA.\tReplace air ducts in accordance with Boeing Service Bulletin 737-21-1085, dated February 14, 1986, or later FAA-approved revisions. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the applicable service bulletin from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. 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. \n\n\tThis amendment becomes effective October 2, 1986.
83-10-06 R1: 83-10-06 R1 PILATUS BRITTEN-NORMAN LTD: Amendment 39-4656 as amended by Amendment 39-5507. Applies to Models BN-2, BN-2A and BN-2B Islander Series (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent structural failure of the elevator trim tabs, accomplish the following: a) For those airplanes not incorporating Mod NB/M/1117, within the next 10 hours time-in-service after the effective date of this AD or within 10 hours time-in-service from the last inspection per AD 83-07-03 and thereafter at intervals not to exceed 10 hours time-in-service: 1) Visually inspect, using a 5x power magnifying glass, the elevator trim tab skins, front channel member (spar) and drive ribs for cracks in accordance with the instructions contained in the "inspection" section of Pilatus Britten-Norman Ltd., Service Bulletin (S/B) No. BN-2/SB.142, Issue 4, dated January 22, 1986 (hereinafter referred to as the S/B), or an FAA-approved equivalent. 2) Visually inspect elevator trim tabs for loose or broken rivets. 3) Visually inspect elevator trim tab hinges for damage or excessive wear. 4) Visually inspect the trim tab operating system for backlash in accordance with the instructions provided in the "Inspection" section of the SB. 5) Before further flight, repair any defects found during accomplishment of paragraphs a)1), a)2), a)3), or a)4) of this AD, in accordance with the instructions contained in the "Rectification (Pre-Mod NB/M/1117 Long Span Tabs)" section of the SB and/or instructions provided by Pilatus Britten-Norman, Ltd., Bembridger, Isle of Wight, England, and approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. 6) The actions required by paragraphs a)1) through a)4) of this AD may be performed by the pilot, providing: i) The pilot's logbook has been endorsed by a properly rated mechanic stating that the pilot has been trained to conduct these inspections in accordance with this AD, and ii) These inspections are performed at least once each 100 hours time-in-service by a properly rated mechanic. b) For those airplanes which have incorporated Mod. NB/M/1117, the intervals between repetitive inspections specified in paragraph a) of this AD may be increased to 100 hours time-in-service (as prescribed in the Airplane Maintenance Schedules (Pub. Ref. MS/1 and MS/4), and with the instructions in the Airplane Maintenance Manual (Pub. Ref. MM/1)). c) Any airplane which incorporates a Collins AP107 Autopilot (Mod NB/M/911) is not eligible for incorporation of Mod NB/M/1117 unless the autopilot system has been modified to conform with Appendix 6 (Issue II or later) of Mod NB/M/911 in accordance with SB No. BN- 2/SB156, dated March 14, 1983. d) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. e) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. 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 copies of the document referred to herein upon request to Pilatus Britten-Norman Ltd., Bembridge, Isle of Wight, England; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-4656 superseded AD 83-07-03, Amendment 39-4602. Amendment 39- 4656 became effective on June 2, 1983. This amendment, 39-5507, becomes effective on February 12, 1987.
2004-26-06: This amendment adopts a new airworthiness directive (AD), that is applicable to certain Boeing Model 767-300 and 767-300F series airplanes equipped with General Electric or Pratt & Whitney engines. This AD requires reworking the wing-to-strut diagonal braces and the aft pitch load fittings of the wings, and reinstalling the diagonal braces with new fuse pins and associated hardware. This action is necessary to prevent undetected loss of the diagonal brace fuse pins of the wings and consequent increased loads in other wing-to-strut joints, which could result in separation of the struts and engines from the wings. This action is intended to address the identified unsafe condition.
2023-11-09: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GVII-G500 and GVII-G600 airplanes. This AD was prompted by reports of two landing incidents in which the alpha limiter engaged in the landing flare in unstable air, resulting in high rate of descent landings and damage to the airplanes. This AD requires updating the flight control computer (FCC) software. The FAA is issuing this AD to address the unsafe condition on these products.
97-03-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9 series airplanes, that currently requires repetitive visual inspections to detect corrosion and cracking of the fuselage upper skin and frames in the area of the loop antenna assemblies of the automatic direction finder (ADF), and repair, if necessary. This amendment adds a requirement to perform a visual and an eddy current inspection of the fuselage forward upper skin under the antennas, followed by the reinstallation of the ADF antennas using an improved procedure. This amendment is prompted by the development of a modification of the ADF antenna installation that constitutes terminating action for the required repetitive visual inspections. The actions specified by this AD are intended to prevent rapid decompression of the fuselage, significant structural damage, and subsequent reduced structural integrity of the airplane, due to problems associated with corrosion and fatigue cracking in the subject area.
2005-01-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing airplanes listed above. This AD requires repetitive detailed inspections of the midspar web of the inboard and/or outboard struts for cracking, disbonding, or buckling; repetitive detailed inspections of the midspar stiffeners for any crack or fracture; related investigative actions; and corrective actions, if necessary. This AD is prompted by reports of cracking in the midspar web. We are issuing this AD to detect and correct cracking in the midspar assembly, which could result in the loss of the midspar assembly load path, and could, combined with the loss of the nacelle station 180 bulkhead load path, lead to the separation of the engine from the airplane.
61-16-02: 61-16-02 ARMSTRONG-WHITWORTH: Amdt. 315, Part 507 Federal Register August 3, 1961. Applies to the following Model AW-65O Argosy Series 101 aircraft only: Serial Numbers 6655, 6656, 6657, 6659, and 6660. Compliance required as indicated. Because of service defects found on the elevators, rudders, fins and flaps, the following is required: (a) Prior to every flight, visually inspect the following areas for loose rivets, cracks and damaged skin: (1) Top and bottom surface of both elevators including horn balances. (2) Inboard and outboard sides of left and right fins. (3) Entire surface of left and right rudders including tabs. (4) Undersurface of inboard flaps. (b) If loose rivets or damaged skin is found an FAA approved repair must be accomplished prior to further flight. (c) If cracks are found, the following action must be taken: (1) If cracks between adjacent rivets or cracks at least one inch long are found, the internal structure in that location must be inspected. If no internal damage is found, an FAA approved repair must be made to the skin prior to the next flight. If any internal damage is found the component must either be replaced or an FAA approved repair incorporated prior to next flight. (2) If cracks less than one inch long and less than twelve inches apart are found, they must be repaired prior to the next flight. Cracks less than one inch long which are twelve inches or more apart must either be stopped by drilling or repaired prior to next flight. (d) The special inspections in (a), (b), and (c) are no longer required when AWA modifications 650/686, 650/687, 650/688, 650/689, and 650/690 are all incorporated. This supersedes AD 61-05-01. This directive effective August 3, 1961.
2023-09-09: The FAA is adopting a new airworthiness directive (AD) for turbocharged, reciprocating engine-powered airplanes and helicopters and turbocharged, reciprocating engines with a certain v-band coupling installed. This AD was prompted by multiple failures of spot-welded, multi-segment v-band couplings at the tailpipe to the turbocharger exhaust housing flange (also referred to as ''spot-welded, multi- segment exhaust tailpipe v-band coupling''). This AD establishes a life limit for the spot-welded, multi-segment exhaust tailpipe v-band coupling and requires repetitively inspecting the spot-welded, multi- segment exhaust tailpipe v-band coupling. The FAA is issuing this AD to address the unsafe condition on these products.
97-03-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 and 737 series airplanes, that requires replacing the fuel cap assembly with a new assembly on the inlet fitting at the inside top of the Boeing-designed auxiliary fuel tank(s). This amendment also requires installing certain new placards once the replacement action is accomplished. This amendment is prompted by reports that the fuel cap assembly, due to its design, became loose and allowed fuel to enter the deactivated auxiliary fuel tanks on in-service airplanes. The actions specified by this AD are intended to prevent unwanted fuel transferring to the deactivated auxiliary fuel tanks, due to the problems associated with a loose fuel cap assembly.
88-13-07: 88-13-07 SHORT BROTHERS, PLC: Amendment 39-5950. Applies to Model SD3-30 series airplanes; serial numbers SH3002 through SH3096, inclusive; certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent pitot tubes from becoming inoperative due to icing, which could result in erroneous airspeed and altitude indication, accomplish the following: A. Within the next 180 days after the effective date of this AD, replace pitot tubes having the code letter "Z" adjacent to the serial number with one containing a code letter other than "Z", in accordance with accomplishment instructions in Service Bulletin SD3-34-26, Revision 1, dated September 1, 1985. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, 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 may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. 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 requirements required by 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 Short Brothers, PLC, Service Representative, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. This information 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, 39-5950, becomes effective July 11, 1988.
2004-26-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-215-6B11 (CL215T variant) and CL-215-6B11 (CL415 variant) series airplanes. This AD requires replacing the mounting pad studs of the auxiliary feather pump with new, longer studs, and installing a pressure relief valve. This AD is prompted by a few incidents of external oil leaks from the oil pump of the power control unit due to a malfunction of the pressure regulating valve. We are issuing this AD to prevent fracturing of the pump body, which could result in loss of engine oil, and consequent inability to maintain engine oil pressure and to feather the propeller.