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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.
88-02-05: 88-02-05 SOCATA: Amendment 39-5829 applies to Models TB 20 and TB 21 (Serial numbers 275 through 709) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To detect interference between the moveable portions of the landing gear structure that may prevent extension of the landing gear, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) visually and tactilely (by touch) inspect the main landing gear hinge ball joints for play or interference marks between the articulated strut and the main landing gear box stiffeners as described in SOCATA TB Aircraft Service Bulletin (SB) No. 30, dated, December 1986. (1) If detectable play is observed in the hinge ball joints in interference marks are found on the articulated strut or landing gear stiffener box, before further flight modify the airplane as prescribed in SOCATA TB Aircraft S/B No. 30, dated December 1986. (2) If no looseness or interference is found, within 100 hours TIS after the effective date of this AD modify the airplane as prescribed in SOCATA TB Aircraft SB No. 30, dated December 1986. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000, Brussels, Belgium; Telephone 513.38.30. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to SOCATA Groupe AEROSPATIALE, B.P 38, 65001 Tarbes, France; Telephone 62.51.73.00 or 62.93.99.45 (for recorder); or Mr. Bernard H. Veyssiere, Deputy Product Support Manager, U.S., Aerospatiale, 2701 Forum Drive, Grand Prairie, Texas 75053; Telephone (214) 641.3614; or may examine the document(s) referred to herein at FAA, Office of the RegionalCounsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on February 20, 1988.
79-22-04: 79-22-04 GULFSTREAM AMERICAN CORPORATION (GAC): Amendment 39-3600. Applies to GAC Model AA-5, serial numbers AA5-0001 and subsequent, Model AA-5A, serial numbers AA5A-0001 and subsequent, Model AA-5B, serial numbers AA5B-0001 and subsequent, airplanes certificated in all categories, except those aircraft modified in accordance with AD 79-16-05 which required GAC Service Kit 150 be installed. Compliance is required as indicated, unless already accomplished. To prevent possible aileron oscillation, accomplish paragraphs (a) and (b) or paragraphs (a), (c), and (d): (a) Inspect the aileron system within 25 hours time in service after the effective date of this AD as follows: (1) Inspect aileron trim tabs for loose rivets and general condition. Replace or repair as necessary. (2) Inspect the aileron for damage or delamination. Repair and rebalance as necessary per GAC AA-5 series Service Manual. (3) Inspect aileron bearings and stops for wear, damage, andsecure mounting. Repair per GAC AA-5 series Service Manual. (4) Inspect and adjust rigging and cable tension per GAC AA-5 series Service Manual. (5) Inspect aileron torque tubes for wear and loose joints. Repair per GAC AA-5 series Service Manual. (b) Repeat the inspection in (a) every 100 hours time in service. (c) Within 25 hours time in service after the effective date of this AD, modify the aileron in accordance with: (1) GAC Service Kit No. 150 dated July 13, 1979, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, or (2) An equivalent method of compliance if approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. (d) If the modification in (c)(1) is accomplished, any autopilot system installed in the aircraft must be disconnected prior to further flight in a manner which will not permit use or reconnection during flight. Install a placard in full view of the pilot utilizing a minimum of 1/4 inch high letters with the wording "AUTOPILOT DEACTIVATED." The use of the autopilot system is prohibited until the STC holder provides instructions for reactivation which have been approved by the Chief, Engineering and Manufacturing Branch of the appropriate FAA Regional Office. (e) The repetitive inspections required by paragraphs (a) and (b) are not required when the aircraft is modified in accordance with paragraph (c). (f) Make appropriate maintenance record entry. This supersedes Amendment 39-3524, AD 79-16-05, as amended by Amendment 39-3586. This Amendment 39-3600 is effective November 9, 1979.
64-27-03: 64-27-03 SUD AVIATION: Amdt. 39-8 Part 39 (New) Federal Register December 2, 1964. Applies to Model SE 210 Caravelle VIR Aircraft. Compliance required as indicated. In order to prevent fatigue failure of the main landing gear steel axle beams accomplish the following: (a) Within 430 hours' time in service after the effective date of this AD and thereafter at intervals not exceeding 430 hours' time in service from the last inspection, visually inspect all main landing gear steel axle beams, P/N's 269028B and 269029B, for cracks around threaded holes, as specified in Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963. (Note: This inspection may be made without disassembly of tubing support components.) (b) Within 860 hours' time in service after the effective date of this AD and thereafter at intervals not exceeding 860 hours' time in service from the last inspection, remove the lower tubing support shield and visually inspect witha magnifying glass the lower threaded holes in the main landing gear steel axle beams for cracks. (c) Unless previously accomplished remove the lower tubing support shielding and inspect for cracks all lower threaded holes in the main landing gear steel axle beams and surrounding areas using fluorescent magnetic particle inspection or FAA approved equivalent at the following times: (1) For landing gear with between 4,500 hours' and 5,100 hours' total time in service as of the effective date of this AD accomplish the inspection before the accumulation of 5,530 hours' total time in service. (2) For landing gear with 5,100 or more hours' total time in service as of the effective date of this AD accomplish the inspection within 430 hours' total time in service after the effective date of this AD. (d) Within 8,000 hours' total time in service rework all the lower threaded holes on axle beams as specified in Hispano Suiza Aero-service Bulletin No. 91 Section 1, No. 34dated January 4, 1963, or an FAA approved equivalent. The repetitive inspections specified in (b) and the inspection specified in (c) need not be performed after this rework has been accomplished. (e) Within 12,000 hours' total time in service rework in accordance with Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, or an FAA approved equivalent all holes in the landing gear which have not previously been reworked in accordance with (d). This AD no longer applies to aircraft on which this rework has been accomplished. (f) Replace any parts found cracked before further flight. (g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Division, Paris, France, 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 forsuch operator. (Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, covers this same subject.) This directive effective January 1, 1965.
2019-12-05: The FAA is adopting a new airworthiness directive (AD) for certain CFM International S.A. (CFM) CFM56-5B, CFM56-5C, and CFM56-7B model turbofan engines with a certain rotating air high-pressure turbine (HPT) front seal. This AD requires replacement of the affected rotating air HPT front seal with a part eligible for installation. This AD was prompted by cracks found in the rotating air HPT front seal. The FAA is issuing this AD to address the unsafe condition on these products.