Results
2019-21-11: The FAA is superseding Airworthiness Directive (AD) 2019-19-11 for certain Pratt & Whitney (PW) PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines. AD 2019-19-11 required initial and repetitive inspections of the low-pressure compressor (LPC) inlet guide vane (IGV) and the LPC rotor 1 (R1) and, depending on the results of the inspections, possible replacement of the LPC. This AD requires the same inspection of the LPC R1 for cracks or damage, removes the inspection of the LPC IGV for proper alignment, and expands the applicability to certain additional PW turbofan engines. This AD also reduces the compliance time for these inspections for certain PW turbofan engines. This AD was prompted by recent findings of cracks in the LPC R1 and an additional in-flight failure of the LPC R1. The FAA is issuing this AD to address the unsafe condition on these products.
82-15-07: 82-15-07 ROBINSON HELICOPTER COMPANY: Amendment 39-4419. Applies to Model R-22 series helicopters certificated in all categories, serial numbers 0002 through 0282. Compliance is required as indicated, unless already accomplished. To prevent loss of power to the tail rotor, accomplish the following: Within 100 hours' additional time in service after the effective date of this AD, remove from further service the following tail rotor drive shaft components in accordance with Robinson Helicopter Company Service Bulletin No. 21 dated June 1, 1982, or FAA approved equivalent: T/R Driveshaft Assembly A197-* thru Rev. P, Damper Assembly A041-1 thru Rev. H, Plate, Flex Coupling A193-3, Spacer A559-1 thru Rev. F, Spacer A559-2. Replace with: T/R Driveshaft Assembly A197-* Rev. Q and subsequent, Damper Assembly A041-1 Rev. I and subsequent, Plate, Flex Coupling A947-3, Spacer A559-1 Rev. G and subsequent. *The dash number of the replacementA197 shaft must be the same as the one removed to obtain the correct length. Special flight permits may be issued in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations to operate rotorcraft to a base for the accomplishment of modification required by this AD. Alternate inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region. This amendment becomes effective July 26, 1982.
2007-12-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: * * * discovery of interferences between the power wire supplying the galley's coffee-maker and the surrounding structure. These interferences might, by chafing and degrading the wire insulation, generate short circuits between the wire and the aircraft ground through the composite cabinet structure, without activation of the Circuit Breaker (C/B). Several hot spots may then be created and generate a large amount of thick smokes just behind the cockpit. We are issuing this AD to require actions to correct the unsafe condition on these products.
84-08-01: 84-08-01 SIKORSKY AIRCRAFT DIVISION: Amendment 39-4846. Applies to all Sikorsky Model S-76A helicopters, certificated in all categories, that are equipped with Part Number (P/N) 76000-05100-043, or -045 tail rotor pitch control shaft assemblies. Compliance is required within 25 hours time in service after the effective date of this AD unless already accomplished within the last 75 hours time in service and thereafter at intervals not to exceed 100 hours time in service from the last inspection. To prevent possible failure of the tail rotor pitch control shaft bearing assembly and subsequent partial loss of directional control of the helicopter, accomplish the following: (a) Inspect the tail rotor pitch control shaft bearing assembly for axial movement in accordance with Paragraph E of Sikorsky Alert Service Bulletin (ASB) No. 76-66-18, as revised by ASB No. 76-66-18A, or with an equivalent procedure approved under paragraph (c) of this AD. (b) If the control shaft assembly axial movement exceeds 0.010 inch, replace with a serviceable assembly in accordance with Paragraph E of Sikorsky ASB No. 76-66-18, as revised by ASB No. 76-66-18A, or with an equivalent procedure approved under paragraph (c) of this AD. (c) Upon submission of substantiating data and upon request by an owner or operator through an FAA maintenance inspector, the repetitive inspection interval of this AD may be adjusted and an equivalent method of compliance with this AD may be approved by the Manager, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone number (617) 273-7329. (Sikorsky S-76 Maintenance Manual SA 4047-76-2-1, 5-20-00, Item No. 22, page 30A, March 12, 1984, pertains to the repetitive inspection.) This amendment becomes effective April 24, 1984.
88-22-07: 88-22-07 CESSNA: Amendment 39-6050. Applies to all TP206, TU206, T207, T210 and P210 Series airplanes (all serial numbers) certificated in any category. Compliance: Required within the next 75 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent power loss or fire due to failure of certain Aeroquip 601 hose assemblies, accomplish the following: (a) Visually inspect all of the exterior metal braided flex hose assemblies, including firesleeve hose assemblies, in the engine compartment. If the Aeroquip Part Number AE701 appears on the hose identification tag, no further action is required per this AD. (b) If the hose identification tag displays the model/part number suffix 601, accomplish the following: (1) Determine if the hose is identified with a cure date 1Q84 through 3Q87. NOTE: The cure date refers to the quarter and year of manufacture, for example, 1Q84 refers to a hose manufactured in the firstquarter of 1984. (2) Review the airplane/engine log books or records to determine if any engine compartment Model 601 hose was replaced between April, 1984 and May, 1988. (3) If the hose identification tag indicates that the hose was not manufactured with a cure date of 1Q84 through 3Q87 and the above review of the log books indicates that no Model 601 hoses were replaced between April, 1984 and May, 1988, no further action is required per this AD. (4) If any engine compartment Model 601 hose displays a manufactured code date of 1Q84 through 3Q87, if there is no manufacturing code tag, or the engine/airplane logs/records indicate that a Model 601 hose was installed between April 1984, and May, 1988, replace the suspect hoses as follows: (i) Prior to further flight replace the waste gate supply hose assembly, Aeroquip P/N 601000-4-0310 or the hose identified as Cessna S1236-4-0310 supplied by sources other than Cessna, or as identified above with an AeroquipP/N AE3663162E0310 hose or equivalent in accordance with Cessna Service Bulletin SEB 88-5, dated June 24, 1988, or with an Aeroquip 601000-4-0310 hose assembly displaying a manufacturing cure date of 4Q87 or subsequent. (ii) Within the next 12 calendar months, replace all other suspect Aeroquip 601 type hose assemblies in the engine compartment with a serviceable hose displaying a manufacturing cure date of 4Q87 or subsequent. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used, if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this AD may obtain copies of the documents referred to herein upon request to the Cessna Aircraft Company, Piston Aircraft Marketing Division, P.O. Box 1521, Wichita, Kansas67201. These documents may also be examined at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-6050, becomes effective on November 24, 1988.
2019-20-09: The FAA is superseding Airworthiness Directive (AD) 2011-18- 15, which applied to certain De Havilland Aircraft of Canada Limited Model DHC-8-400 series airplanes. AD 2011-18-15 required initial and repetitive torque checks of the bolt preload; detailed inspection of the barrel nuts and cradle for cracking, pitting, and corrosion if the bolt preload is correct; and replacement of certain hardware if necessary. This AD continues to require those actions. This AD also requires new inspections and replacement of certain hardware, which would terminate the repetitive torque checks and inspections; and removes airplanes from the applicability. This AD was prompted by in- service reports of cracked barrel nuts found at the front spar locations of the wing-to-fuselage attachment joints, and a loose washer in the barrel nut assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2019-20-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-243, -243F, -341, -342, and -343 airplanes. This AD was prompted by a determination that cracks can develop on the ripple damper weld of the hydraulic pressure tube assembly and reports of failure of the ripple damper of the hydraulic pressure tube assembly. This AD requires replacement of the affected hydraulic pressure tube assembly or modification of both engines, 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.
99-01-15: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A340-211, -212, -213, -311, -312, and -313 series airplanes. This action requires repetitive operational tests to ensure proper operation of the actuator of the secondary locks of the thrust reversers; and corrective actions, 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 the inadvertent opening of a thrust reverser door in the event of failure of the primary and secondary locks of the thrust reverser. Such inadvertent opening could result in reduced controllability of the airplane.
85-19-03 R2: 85-19-03 R2 MCDONNELL DOUGLAS: Amendment 39-5137 as amended by Amendment 39-5200 is further amended by Amendment 39-5844. Applies to McDonnell Douglas Model DC-9, DC-9-80, and C-9 (Military) series airplanes, fuselage numbers 1 through 1371, certificated in any category, with more than 30,000 landings.\n\n\tCompliance required as indicated, unless previously accomplished.\n\n\tA.\tWithin the next 1,600 landings after the effective date of this AD, inspect the skin and doublers around the upper anticollision light cutout for cracks in accordance with McDonnell Douglas Service Bulletin 53-186, dated April 17, 1985 (hereinafter referred to as SB 53-186), Figure 2, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tB.\tIf no cracks are found under Condition I, Phase I, as referenced in SB 53-186, perform repetitive eddy current inspections at intervals not to exceed 3,500 landings in accordance with Figure 2 of SB 53-186, until such time as stress coining of plate nut clearance holes, as outlined under Condition 1, Phase II of SB 53-186, or SB 09530186 (originally identified as McDonnell Douglas DC-9 Service Sketch 3626C), is accomplished.\n\n\tC.\tIf cracks are found, before further flight:\n\n\t\t1.\tFor cracks less than 1.00 inch long, repair cracked area in accordance with Conditions II or III of the Accomplishment Instructions in SB 53-186, or SB 09530186.\n\n\t\t2.\tFor cracks 1.00 to 1.25 inches long, repair cracked area in accordance with Condition III of the Accomplishment Instructions in SB 53-186, or SB 09530186.\n\n\t\t3.\tFor cracks greater than 1.25 inches, repair in accordance with data approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tD.\tTerminating Action. Completion of the Accomplishment Instructions of SB 53-186, or SB 09530186, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, constitutes terminating action for this AD.\n\n\tE.\tAlternative inspections, modifications, or other actions which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tF.\tUpon request of operator, an FAA maintenance inspector, subject to prior approval of the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, 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 increase for that operator.\n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California.\n\n\tAmendment 39-5137 (AD 85-19-03) became effective October 14, 1985.\n\n\tAmendment 39-5200 (AD 85-19-03 R1) became effective January 19, 1986.\n\n\tThis amendment, 39-5844, becomes effective March 21, 1988.
2019-19-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC225LP helicopters. This AD requires determining the total hours time-in-service (TIS) of the free wheel shafts of certain main rotor gearboxes (MGBs), replacing the MGB or right-hand side (RH) free wheel shaft, installing placard(s), and revising the Rotorcraft Flight Manual (RFM) for your helicopter. This AD was prompted by a report of wear of the ramps of the RH free wheel shaft. The actions of this AD are intended to address an unsafe condition on these products.