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85-24-01: 85-24-01 MCDONNELL DOUGLAS: Amendment 39-5169. Applies to McDonnell Douglas Model DC-8-70 series airplanes, equipped with an auxiliary power unit in accordance with STC SA1387NM. \n\n\tCompliance is required as indicated. \n\n\tTo preclude potential APU exhaust door failures and resulting wiring and structural damage, accomplish the following, unless already accomplished: \n\n\tA.\tWithin six (6) months after the effective date of this AD, complete the modifications defined in McDonnell Douglas DC-8-70 Service Bulletin 49-2, dated May 16, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. The modifications involve removal of the APU; modification of the APU module and control boxes; revision of the APU control system sensing and firex control wiring; replacement of three generator phase circuit breakers; and the APU control and fuel supply circuit breakers; inspection of the wire routing; and reinstallation ofthe APU. \n\n\tB.\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\tC.\tAlternate means of compliance 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\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective December 19, 1985.
2006-25-14: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from 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 describes the unsafe condition as the possible failure of the attachment of the propeller blades. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2019-12-14: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 helicopters. This AD requires establishing or reducing the life limit of various parts. This AD was prompted by recalculations. The actions of this AD are intended to address an unsafe condition on these products.
80-02-02 R2: 80-02-02 R2 BOEING: Amendment 39-3660 as amended by Amendment 39-3863 is further amended by Amendment 39-3970. Applies to Model 737 series airplanes certificated in all categories which have an operative Boeing designed auxiliary body fuel system installed. Compliance required within 600 flight hours from the effective date of this AD unless this initial inspection and test has been previously accomplished within the past 300 flight hours. To prevent failure of the fuel system and unwanted fuel transfer to the auxiliary body fuel tanks, accomplish the following: \n\n\tA.\tInspect and test the auxiliary body fuel tank installation as required and as outlined in Boeing Service Bulletin 737-28A1032 or later FAA approved revisions. If the shrouds are found defective, replace with a serviceable Boeing part or deactivate the system prior to further flight. \n\n\tB.\tRepeat the required inspections and tests every 1500 flight hours after the initial inspection unless the system has been deactivated. If shrouds are found defective, replace with a serviceable Boeing part, or deactivate the system prior to further flight. \n\n\tThe recurring inspection interval may be adjusted upon request of the operator. The FAA Maintenance Inspector, subject to prior approval by the Chief, Engineering and Manufacturing Branch, Northwest Region, may adjust the repetitive inspection interval specified in this AD if the request contains substantiating data to justify the increase.\n \n\tC.\tPrior to reactivating a previously deactivated auxiliary body fuel system, whether deactivated voluntarily or due to defects found in the auxiliary tank fuel system through inspections and tests accomplished in paragraphs A. and B. above, the auxiliary body fuel system must be repaired as required and shown to meet the requirements of paragraph A. and must be reinspected on a recurring basis per paragraph B. \n\n\tD.\tInstallation of the following Boeing final design part numbered refuel and vent line shrouds for the corresponding original and or interim design Boeing Part Number refuel and vent line shrouds will relieve the operator from compliance with the inspection and test requirements outlined in Paragraphs A, B and C above. This constitutes terminating action for the AD. \n\n\n\nOriginal Design\tPart Numbers\nInterim Design Part Numbers\nFinal Design Part Numbers\n10-61707-3\n10-61707-65\n10-61707-651\n-4\n-66\n-661\n-5\n-67\n-671\n-6\n-68\n-681\n-7\n-69\n-691\n-35\n-65\n-651\n-36\n-66\n-661\n-37\n-67\n-671\n-38\n-68\n-681\n-39\n-69\n-691\n-41\n-71\n-711\nNone\n-73\n-731\n\t\t\t\t\t \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received these documents and special tools from the manufacturer, may obtain same upon request to Boeing Commercial Airplane Company, Post Office Box 3707, Seattle, Washington 98124. The service bulletin may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tAmendment 39-3660 became effective January 22, 1980. \n\tAmendment 39-3863 became effective August 12, 1980. \n\tThis amendment 39-3970 becomes effective November 20, 1980.
83-02-01: 83-02-01 DeHAVILLAND: Amendment 39-4551. Applies to Model DHC-3 (Military U-IA) airplanes certificated in any category. COMPLIANCE: Required within 30 days after the effective date of this AD unless already accomplished in the last 11 months, and at intervals not to exceed each 12 months thereafter, unless already accomplished. To prevent corrosive deterioration of the wing strut to fuselage attachment structure, accomplish the following: a) Visually inspect each wing strut tie-bar for internal corrosion in accordance with paragraph 5 in the Inspection Section of Service Bulletin S/B No. 3/37 Rev. "A" dated May 14, 1982 (hereinafter referred to as the Service Bulletin). 1) If no corrosion is found, proceed to the inspection specified in paragraph b) of this AD. 2) If evidence of corrosion is found, prior to further flight, remove corrosion, check for depth of corrosion and inspect for cracks using dye penetrant methods as prescribed in paragraph 6 of the Replacement Section of the Service Bulletin. i. If corrosion is within limits and no cracks are evident, proceed to the inspection in paragraph b) of this AD. ii. If corrosion exceeds limits, or cracks are evident, replace the tiebar with an airworthy part in accordance with the Replacement Section of the Service Bulletin. b) Visually inspect all tie-bar lugs for corrosion in accordance with paragraph 9 of the Inspection Section of the Service Bulletin. 1) If no corrosion is found and paragraph a) of this AD has been complied with the airplane may be returned to service. 2) If evidence of corrosion is found, prior to further flight, remove corrosion, check lug minimum thickness and, using a dye penetrant, check lug for cracks in accordance with paragraphs 9 through 11 of the Inspection Section of the Service Bulletin. i. If lug minimum thickness is within limits and no cracks were found and paragraph a) of this AD above has been complied with, the airplane may be returned to service. ii. If lug minimum thickness does not meet minimum specified thickness or, if cracks are found, prior to further flight, replace the tie-bar in accordance with the Replacement Section of the Service Bulletin. c) The airplane may be flown in accordance with FAR 21.197 to a location where the requirements of this AD may be accomplished. d) An equivalent method of compliance with this AD may be used if approved by the Manager, New York Aircraft Certification Office, ANE-170, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment becomes effective on February 3, 1983.
2019-12-13: The FAA is adopting an airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD requires repetitive checks of the aileron trim actuator bearing for free rotation, repetitive detailed inspections of the aileron trim actuator attachment lug for damage and cracking, and applicable on-condition actions. This AD was prompted by a report of the failure of the aileron trim actuator attachment lug. The FAA is issuing this AD to address the unsafe condition on these products.
85-25-10: 85-25-10 CESSNA AIRCRAFT COMPANY: Amendment 39-5224. Applies to Cessna Model S550 and 552 airplanes, with unit numbers identified below, certificated in any category. MODEL UNIT NUMBERS S550 0001 thru 0048, 0051 thru 0075, 0077, and 0079 552 -0001 thru -0015 Compliance is required as indicated, unless already accomplished. To prevent hazardous accumulation of ice on the wing leading edge and horizontal stabilizer during flight in icing conditions, accomplish the following: A. Prior to further flight: 1. Fabricate and install on the instrument panel, in clear view of the pilot, the following placard, using letters of a minimum of 0.10 inch in height: "FLIGHT INTO KNOWN OR FORECAST ICING PROHIBITED," and operate the airplane accordingly. 2. Revise the Airplane Flight Manual, Section II, Operating Limitations - Operations Authorized to read: "This airplane is approved for day and night, VFR, IFR flight. Flight into known or forecast icing conditions prohibited." This may be accomplished by inserting a copy of this AD in the Airplane Flight Manual. B. Within the next 15 flight hours or 15 days after the effective date of this AD, whichever occurs first, inspect and modify, as necessary, the fluid ice protection system left and right inboard wing installation in accordance with Accomplishment Instruction A. of Cessna Alert Service Letter SLAS550-30-05, dated December 17, 1985. C. Within the next 25 flight hours or 30 days after the effective date of this AD, whichever occurs first, inspect and modify, as necessary, the fluid ice protection system left and right outboard wing and horizontal stabilizer installations in accordance with Accomplishment Instructions B. and C. of Cessna Alert Service Letter SLAS550-30-05, dated December 17, 1985. D. Within 5 days after the required inspection, report any defects found to the Manager, Wichita Aircraft Certification Office, FAA, Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. E. The requirements of paragraphs A.1. and A.2., above, may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplanes owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. F. The requirements of paragraphs A.1. and A.2., above, are terminated upon the accomplishment of paragraphs B. and C. of this AD. G. Airplanes may be flown in accordance with FAR 21.197 and 21.199 to a location where the inspection/modification requirements of the AD can be accomplished. H. Alternate means of compliance with this AD which provides an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affectedby this directive who have not already received these documents from the manufacturer may obtain copies upon request to Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277. These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Wichita Aircraft Certification Office, FAA, Central Region, 1803 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas. This amendment becomes effective February 11, 1986, as to all persons, except those persons to whom it was made immediately effective by priority letter AD 85-25-10, issued December 17, 1985.
87-13-01: 87-13-01 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-5911. Applies to Model 222, 222B, and 222U helicopters (LTS 101 series engines installed) certificated in any category. (Airworthiness Docket No. 87-ASW-23) Compliance is required as indicated, unless already accomplished. To detect and prevent a possible impending engine power turbine wheel burst which could result in failure of the adjacent engine, severance of the tail rotor driveshaft, and subsequent loss of the helicopter, accomplish the following: (a) If the scavenge debris monitor is installed on each engine and is wired to a separate red engine chip light which incorporates a light test feature (as previously required by AD 86-17-12, R1, on Bell 222B and 222U helicopters), accomplish the following before further flight: (1) Revise the FAA-approved Rotorcraft Flight Manual Emergency/Malfunction Procedures, Section 3, by adding the following red engine chip light warning procedure to Table 3-1 (warning lights): Eng 1 - Chip (Red) Shut down affected engine. or Land as soon as practical. Eng 2 - Chip (Red) and add the following warning information: WARNING "IN THE EVENT OF FLUCTUATING OR LOSS OF POWER TURBINE (Np) SPEED INDICATION, SHUT DOWN THE AFFECTED ENGINE AS SOON AS POSSIBLE. LAND AS SOON AS PRACTICAL." (2) Revise the FAA-approved Rotorcraft Flight Manual Normal Procedures - Interior and Prestart Check by adding the following: Eng 1 - Chip (Red), Eng 2 - Chip (Red) Activate light test feature and check illumination. NOTE: The FAA-approved Rotorcraft Flight Manual Emergency/ Malfunction Procedures, Section 3, Table 3-2 (caution lights), Eng 1 - Chip (Amber), Eng 2 - Chip (Amber), does not specify engine shutdown on the basis of the amber chip light alone and should remain unchanged. (b) If the scavenge debris monitor is not installed or is not separately wired, revise the FAA-approved RotorcraftFlight Manual Emergency/Malfunction Procedures, Section 3, Table 3-2 (caution lights), before further flight, by changing the current engine chip light procedure to read as follows: Eng 1 - Chip (Amber) Shut down affected engine. or Land as soon as practical. Eng 2 - Chip (Amber) And add the following warning information: WARNING "IN THE EVENT OF FLUCTUATING OR LOSS OF POWER TURBINE (Np) SPEED INDICATION, SHUT DOWN THE AFFECTED ENGINE AS SOON AS POSSIBLE. LAND AS SOON AS PRACTICAL." NOTE: The scavenge debris monitor may be installed and wired to a separate red engine chip light so that the less stringent requirements of paragraph (a) of this AD apply provided that the details of the chip light wiring modification are approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region, Fort Worth, Texas 76193-0170. (c) If the scavenge debris monitor is not installed or not separatelywired, replace each amber engine chip segment lens no later than December 31, 1987, with a red engine chip segment lens or by an equivalent red light indication which is suitably identified. Once this has been accomplished, remove the flight manual changes prescribed in paragraph (b) of this AD and add the flight manual changes prescribed in paragraph (a)(1) of this AD. (d) An alternate method of compliance or adjustment to the compliance time, which provides an equivalent level of safety, may be used when approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region, Fort Worth, Texas 76193-0170. Priority letter 87-13-01 issued June 19, 1987, superceded priority letter AD 86-17-12 R1 and priority letter AD 87-10-04 and was effective upon receipt. This amendment 39-5911 becomes effective May 27, 1988, as to all persons except those persons to whom it was made immediately effective by priority letter AD No. 87-13-01, issued June 19, 1987, which contained this amendment.
2019-12-12: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Model PA-46-600TP (M600) airplanes. This AD requires inserting a ground operations limitation into the Limitations section of the airplane flight manual (AFM) and installing a placard limiting ground operations. This AD also includes optional actions to terminate the ground operating limitations. This AD was prompted by a report of understrength rivets installed during manufacture of the bulkhead assembly. The FAA is issuing this AD to address the unsafe condition on these products.
70-26-06: 70-26-06 PIPER AIRCRAFT: Amdt. 39-1132. Applies to Piper Aircraft Models PA-31 and PA-31-300 Serial Numbers 31-2 through 31-694, certificated in all categories. Compliance required as indicated. To detect cracks in the elevator and rudder spars, and elevator butt ribs accomplish the following: (a) Within the next 100 hours in service after the effective date of this Airworthiness Directive, unless already accomplished within the last 100 hours in service, and thereafter at intervals not to exceed 100 hours in service, inspect in accordance with Piper Service Bulletin No. 323 dated 21 September 1970 and later changes thereto, or in accordance with an equivalent inspection program approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) If cracks are found, the defective parts must be replaced as specified in Piper Service Bulletin No. 323 dated 21 September 1970 and later changes thereto or replaced or repaired in a manner approvedby the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be made. (c) Upon the incorporation of Piper Elevator and Rudder Hinge Installation Kit No. 760 465 or equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, the repetitive inspection required under Paragraph (a) may be discontinued. (d) Report the results of inspection findings required by this Airworthiness Directive to the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, (Reporting approved by Bureau of the Budget under BOB No. 04-R0174). This amendment is effective December 29, 1970.