Results
2006-12-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus transport category airplanes. This AD requires replacing the existing vent float valve with a new, improved vent float valve. This AD results from reports of failure of the vent float valve in the left-hand outboard section of the trimmable horizontal stabilizer. We are issuing this AD to prevent, in the event of a lightning strike to the horizontal stabilizer, sparking of metal parts and debris from detached and damaged float valves, or a buildup of static electricity, which could result in ignition of fuel vapors and consequent fire or explosion.
98-04-44: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires replacement of the groove pins on the doors of the center main landing gear (MLG) with new pins, modification of the bolt head, installation of an antirotation plate, and modification of the hinge pins on the doors of the MLG by the installation of oversize bolts. 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 detachment of the center MLG door during flight, which could pose a hazard to persons or property on the ground.
2000-11-19 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Boeing Model 767-200 and -300 series airplanes. That AD currently requires repetitive inspections to detect wear or damage of the door latches and disconnect housings in the off-wing escape slide compartments, and replacement of any discrepant component with a new component. This new AD revises the applicability of the existing AD to refer to a later revision of the referenced service bulletin, which removes airplanes that are not subject to the identified unsafe condition. This AD results from reports of worn and damaged door latches and disconnect housings in the off-wing escape slide compartments. We are issuing this AD to ensure deployment of an escape slide during an emergency evacuation. Non-deployment of an escape slide during an emergency could slow down the evacuation of the airplane and result in injury to passengers or flightcrew. We are also issuing this AD to detect damaged disconnect housings in the off-wing escape slide compartments, which could result in unexpected deployment of an escape slide during maintenance, and consequent injury to maintenance personnel. \n\nDATES: The effective date of this AD is July 18, 2000. \n\n\tThe Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767-25A0260, Revision 1, dated January 25, 2001; Boeing Service Bulletin 767-25A0260, Revision 2, dated August 26, 2004; Boeing Service Bulletin 767-25A0260, Revision 3, dated July 7, 2005; and Boeing Service Bulletin 767-25A0275, Revision 3, dated April 24, 2003; listed in the AD as of July 17, 2006. \n\n\tOn July 18, 2000 (65 FR 37015, June 13, 2000), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-25A0260, dated July 9, 1998.
2009-01-11: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Several cases of loss of internal components from the Hydro Mechanical Unit (HMU) low fuel pressure switch Hydra-Electric part number (P/N) 9 550 17 956 0 into the fuel system, have been reported on Arriel 2 engines. The loss of internal components from the low fuel pressure switch into the fuel system may lead to a rupture of the HP-LP pumps drive shaft shear pin, and thus to a possible uncommanded in-flight shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD results in an emergency autorotation landing and in certain conditions may lead to an accident. We are issuing this AD to prevent forced autorotation landing, or an accident.
2018-22-11: We are adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran Helicopter Engines), ASTAZOU XIV B and H model engines with certain 3rd-stage turbine wheels installed. This AD requires initial and repetitive inspections of the 3rd-stage turbine wheels. This AD was prompted by a report that six 3rd-stage turbine wheels were returned to service after a repair that could result in exceedance of the allowable vibration threshold during operation. We are issuing this AD to address the unsafe condition on these products.
91-01-05: 91-01-05 BOEING: Amendment 39-6850. Docket No. 90-NM-155-AD. \n\n\tApplicability: Boeing Model 757 series airplanes, as listed in Boeing Service Bulletin 757-25-0061, Revision 2, dated June 29, 1989, certificated in any category. \n\n\tCompliance: Required within 60 days after the effective date of this AD, unless previously accomplished. \n\n\tTo reduce the potential for reduced passenger evacuation capability during an emergency, accomplish the following: \n\n\tA.\tModify the number 3 left and right emergency exit doors by replacing the door catch assembly support and performing an operational check, in accordance with Boeing Service Bulletin 757-25-0061, Revision 1, dated June 9, 1988, or Revision 2, dated June 29, 1989. \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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: Therequest should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tC.\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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6850, AD 91-01-05) becomes effective on January 31, 1991.
87-11-08 R1: 87-11-08 R1 AEROSPATIALE: Amendment 39-5628 as amended by amendment 39-5984. Applies to ATR-42 series airplanes, certificated in any category, unless the equivalent of Production Modification 1397 was installed prior to delivery. Compliance is required as indicated, unless previously accomplished. To prevent simultaneous loss of both pilots' primary attitude and heading information generated by Attitude and Heading Reference Systems (AHRS), accomplish the following: A. Within 15 days after June 8, 1987 (the effective date of Amendment 39-5628, AD 87-11-08), accomplish the following: 1. Isolate the pilots' AHRS (AHRS Number 1) from the System Avionics Standard Communications Bus (ASCB) in accordance with Aerospatiale Service Bulletin ATR- 42-34A-0016, dated March 23, 1987, and ensure that Electronic Flight Instrument System (EFIS) Symbol Generators having part number 700544-411, Mod-level U or subsequent, have been installed. 2. Insert the following intothe Airplane Flight Manual (AFM) Limitations Section 2. This can be accomplished by inserting a copy of this AD into the AFM and into the Flight Crew Operations Manual (FCOM), if used. a. "Disconnect autopilot at or above 200 feet above ground level (AGL)." b. "Approach operations are limited to Category I or higher weather minima." B. Replacement of the Attitude and Heading Reference Systems (AHRS) with a modified AHRS, and connection of four (4) wires between terminal blade 67VT1 and connector 1FP1-AA, in accordance with Aerospatiale Service Bulletin ATR42-34-340018, Revision 1, dated September 22, 1987, constitutes terminating action for the requirements of paragraph A., above. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAAPrincipal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. 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 39-5984 amends AD 87-11-08, Amendment 39-5628. This Amendment, 39-5984, becomes effective September 3, 1988.
87-23-03: 87-23-03 BRITISH AEROSPACE: Amendment 39-5757. Applies to all Model Viscount 700, 800, and 810 series airplanes which have accumulated more than 10,000 landings, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of the wing due to cracking, accomplish the following: A. Before further flight: 1. Visually inspect the wing upper surface and end rib in accordance with applicable British Aerospace Preliminary Technical Leaflet No. 185 or No. 316, both dated October 23, 1986. Repeat this inspection at intervals not to exceed 25 landings. 2. Perform eddy current inspection of the wing in accordance with applicable British Aerospace Preliminary Technical Leaflet No. 185 or No. 316, both dated October 23, 1986. Repeat this inspection at intervals not to exceed 1,500 landings. B. Any cracks found as a result of the inspections required by paragraph A., above, must be repaired prior to further flight in a manner approved by the FAA. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Eddy current inspections may be deferred for 15,000 landings after incorporation of Modification D3292 or Modification FG2172 as applicable. All persons affected by this proposal who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment becomes effective December 9, 1987.
89-02-01 R1: 89-02-01 R1 MCDONNELL DOUGLAS HELICOPTER COMPANY (HUGHES HELICOPTER, INC.): Amendment 39-6051 as revised by Amendment 39-6341. Docket No. 88-ASW-43. Applicability: Model 369D, E, F, and FF helicopters, certificated in any category, with main rotor hub retention straps having part number (P/N) 369D21210-BSC or -501 installed. Compliance: Required as indicated, unless already accomplished. (a) Within the next 100 hours' time in service and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, conduct inspections of the main rotor blade retention strap assemblies (P/N) 369D21210-BSC, or -501, in accordance with paragraphs a, b, c, d, e, g, i, j, and 1 of Part I, Inspection Procedures, in McDonnell Douglas Helicopter Company Service Information Notice (SIN) DN-154 (369D), EN-44 (369E) or FN-33 (369F and 369FF), dated January 15, 1988. (b) If, as a result of an inspection in paragraph (a) above, two strap pack laminates are determined to have failed in any one leg or tongue area of any strap assembly (failure being defined in the applicable SIN under CAUTION following paragraph e of Part I, Inspection Procedures), conduct the repetitive inspections of all strap packs required in paragraph (a) above and thereafter at intervals not to exceed 25 hours' time in service. (c) For Model 369D hub assemblies (P/N 369D21200) which were subject to inspections under AD 77-15-09 R1 at intervals of 25 hours because of two strap pack laminate failures, conduct the inspections required by this AD within 25 hours' time in service from the last inspection made in accordance with AD 77-15-09 R1, and thereafter at intervals not to exceed 25 hours' time in service. (d) For Model 369D hub assemblies (P/N 369D21200) which were subject to inspections under AD 77-19-04 (retention straps with P/N 369D21210-BSC) at intervals of 25 hours, conduct the inspections required by this AD within 25 hours' time in service from the last inspection made in accordance with AD 77-19-04, and thereafter at intervals not to exceed 25 hours' time in service. (e) For Model 369D hub assemblies, P/N 369D21200, which were subject to inspections under AD 81-10-08 (retention straps with P/N 369D21210-501, S/N 8531 through 9135) at intervals of 25 hours' time in service, conduct the inspections required by this AD within 25 hours' time in service from the last inspection made in accordance with AD 81-10-08, and thereafter at intervals not to exceed 25 hours' time in service. (f) Replace the hub assembly, P/N 369D21200, with a serviceable assembly prior to further flight if, as a result of the inspection of paragraph (a), (b), (c), (d), or (e) above, a strap pack, P/N 369D21210-BSC or -501, is rejected (using the rejection criteria in the applicable SIN under CAUTION following paragraph e of Part I - Inspection Procedures). (g) For strap packs which contain observed damage but are not rejected by the criteria of paragraph (f)-- (1) Record in the maintenance record (Ref. Section 43.9) the locations of observed cracks, fractures, or corrosion in each strap laminate in a manner which includes-- (i) Blade color; (ii) Strap part numbers and serial number; (iii) Laminate number (top being number one); (iv) Leg location (lead or lag); and (v) Tongue location (The tongue location is not the same as the outboard end). NOTE: Strap packs containing cracks in outboard end locations are rejected by the criteria of paragraph (f). (2) Record for each strap pack-- (i) The number of laminate failures; (ii) The number of laminates cracked in the same leg; and (iii) The number of gaps. Airworthiness Directive 89-02-01 superseded the following: AD 77-15-09, Amendment 39-2978 (42 FR 37806; July 25, 1977) as amended by AD 77- 15-09 R1, Amendment 39-3952 (45 FR 70848; October 27, 1980) which was effective October 30, 1980. AD 77-19-04, Amendment39-3039 (42 FR 46923; September 19, 1977), as amended by AD 77-19-04 R1, Amendment 39-3597 (44 FR 61936; October 26, 1979) which was effective November 1, 1979. AD 81-10-08, Amendment 39-4144 (46 FR 33225; June 29, 1981) which was effective June 30, 1981, to all persons except to those to whom it was made immediately effective by priority letter AD 81-10-08 issued May 5, 1981. Amendment 39-6341 revises Amendment 39-6051 (54 FR 105; January 4, 1989), AD 89- 02-01, which became effective on February 2, 1989. Amendment 39-6341, AD 89-02-01 R1, became effective on October 27, 1989. A correction to reflect a change to paragraph (d) became effective on July 19, 1990. This correction is issued to reflect AD's previously superseded by AD 89-02-01, which were inadvertently omitted from AD 89-02-01 R1.
89-05-02: 89-05-02 BEECH: Amendment 39-6144. Applicability: The airplanes listed below, certificated in any category: MODELS SERIAL NUMBERS 35-33, 35-A33, 35-B33, 35-C33, E33 CD-1 through CD-1234 35-C33A, E33A CE-1 through CE-289 E33C CJ-1 through CJ-25 35, 35R, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35-TC, V35A, V35A-TC D-1 through D-9068, D-15001 and D-15002 36 E-1 through E-184 95-55, 95-A55, 95-B55, 95-B55A TC-1 through TC-1287 95-C55, 95-C55A, D55, D55A TE-1 through TE-767 56TC TG-2 through TG-83 95, B95, B95A, D95A, E95 TD-2 through TD-721 This AD also applies to any of the following military airplanes which have been modified for civil certification as described on the applicable Federal Aviation Administration Type Certificate Data Sheet or Aviation Specification: T34A, T34B (Commercial Model 45 Series) T42A (Commercial Model 95-B55B) NOTE: The magnesium fittings may have been installed as original equipment or as replacement spares. Compliance: Required as indicated, unless already accomplished. To prevent the failure of the magnesium elevator control fittings, accomplish the following: (a) Within 100 hours time-in-service (TIS) after the effective date of this AD, determine the composition of the elevator control fittings in accordance with the instructions contained in Beech Service Bulletin No. 2242, Revision 1, dated August 1988. (1) If the fittings are determined to be aluminum, no further action is required by this AD. (2) If the fittings are determined to be magnesium, accomplish the actions specified below. (b) At the time of the inspection per paragraph (a), and every 100 hours TIS thereafter, visually inspect each magnesium elevator control fitting for cracks in accordance with the above referenced Service Bulletin. (c) If any fitting is found to be cracked, prior to further flight replace the cracked fitting with an aluminum fitting as described in the above referenced Service Bulletin. (d) The above inspections are no longer required when aluminum fittings have been installed on both elevators. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beechcraft Aero and Aviation Centers; Beech Aircraft Corporation, Commercial Service, Dept. 52, P.O. Box 85, Wichita, Kansas 67201-0085, or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6144, AD 89-05-02) becomes effective on March 24, 1989.