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74-21-04: 74-21-04 HUGHES HELICOPTERS: Amendment 39-1987 as amended by Amendment 39-2147. Applies to Hughes 269A, 269A-1, 269B, 269C Helicopters certificated in all categories, including military TH-55A equipped with canopy slat P/N 269A2297 or 269A2297-7. Compliance required as indicated. To detect possible cracks in canopy slat surfaces, and the condition and security of slat attachment hardware and canopy attachment areas, and provide for modification of the canopy slat, accomplish the following: (a) On each day the helicopter is flown, conduct a close visual check by the pilot in command or an inspection by a certificated mechanic of the canopy slat surfaces over the entire length for cracks, slat attachment hardware and canopy attachment areas for condition and security. Note: The person who performs the check or inspection shall record it in the appropriate aircraft records per FAR 91.173. (1) If cracks or other damage are found, replace prior to further flight with: (i) P/N 269A2297 or 269A2297-7 modified in accordance with (b), below; or (ii) P/N 269A2214; or (iii) If the 50 hour limitation specified by (b), below, has not been exceeded, an unmodified part P/N 269A2297 or 269A2297-7 may be used, provided, it is modified at the time specified by (b), below; or (iv) A part approved by Chief, Aircraft Engineering Division, FAA Western Region. (b) Prior to the next 50 hours time in service after the effective date of this amendment, 39-2147, unless already accomplished, modify the canopy slat, P/N 269A2297 or 269A2297-7, in accordance with the instructions contained in Hughes Service Information Notice N-127, dated March 5, 1975, or later FAA-approved revisions, or equivalent procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Upon installation of P/N 269A2297 or 269A2297-7 modified in accordance with (b), above, or P/N 269A2214 or other part approved by the Chief, AircraftEngineering Division, FAA Western Region, the daily visual check or inspection in accordance with (a) above may be discontinued. Amendment 39-1987, was effective October 16, 1974, for all persons except those to whom it was made effective immediately by airmail letter dated September 23, 1974. This Amendment 39-2147, to AD 74-21-04 becomes effective April 4, 1975.
70-01-02: 70-01-02 CESSNA: Amdt. 39-906. Applies to Models 177 and 177A, Serial Numbers 177- 00001 thru 177-01160, 177-01165 thru 177-01168, 177-01171, 177-01174 thru 177-01178 and 177-01180, airplanes. Compliance: Required as indicated, unless already accomplished. To prevent possible damage to the fuel quantity transmitter float arm during refueling, which can result in inaccurate quantity indication, accomplish the following: Within 50 hours' time in service after the effective date of this AD but no later than March 1, 1970, remove the fuel quantity transmitter from each fuel tank and install new Cessna P/N 12341-667-1 and 12341-667-2 fuel gauge transmitters in accordance with the instructions contained in Cessna Service Letter No. SE69-25. dated December 9, 1969, or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective January 3, 1970.
2005-14-12: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. models HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC- B3MN-3, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, HC-B4MP-3, HC-B4MP-5, and HC- B5MP-3 propellers, installed with propeller mounting bolts, part number (P/N) B-3339. This AD requires initial and repetitive visual inspections and torque checks of certain manufacture lot numbers of propeller mounting bolts, P/N B-3339, and eventual removal from service of those bolts. This AD results from the discovery during routine propeller installation that a bolt from a certain manufacture lot did not properly absorb the installation torque. This AD also results from the discovery that other bolts of the same part number from a different manufacture lot had material surface pitting. We are issuing this AD to prevent propeller attaching bolt failures or improperly secured propellers, which could lead to separation of the propeller from the airplane.
2016-15-02: We are adopting a new airworthiness directive (AD) for all M7 Aerospace LLC Models SA26-AT, SA26-T, SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes. This AD was prompted by reports of multiple cracks in the steel horizontal tube of the cockpit control column. This AD requires inspection of the cockpit control column horizontal tube for cracks and repair or replacement of the cockpit control column as necessary. We are issuing this AD to correct the unsafe condition on these products.
73-07-07: 73-07-07 CESSNA: Amdt. 39-1617. Applies to all Models 310 and 320 series airplanes and Serial Numbers, except Models 310, 310A, 310B and 310Q (Serial Numbers 310Q0710 and up). Compliance: Required as indicted, unless already accomplished. To determine condition of fuel lines, electrical wiring, and to detect loose fittings and attachments, to reduce possible collection of flammable fluids and to eliminate possible ignition sources within the leading edges of the wings, within the next 25 hours' time in service after the effective date of this AD, accomplish the following in accordance with Cessna Multi-engine Service Letter ME73-5 dated March 16, 1973, and Cessna Service Kit SK310-90 dated March 7, 1973, or later FAA approved revisions or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region: 1) Inspect the fuel lines and electrical harnesses in the wing leading edge for corrosion, chafing, looseness, or other unserviceable conditions. Procedures for this inspection are contained in Cessna Service Kit SK 310-90. 2) Prior to further flight replace and/or repair any unserviceable parts or conditions found as result of the above inspection. 3) Install leading edge drainage and sealant provisions in the wings in accordance with Paragraph B of Cessna Service Kit SK 310-90. 4) Remove, relocate and reinstall the auxiliary fuel boost pump resistor and relay in accordance with Paragraphs C and D of Cessna Service Kit SK 310-90. a) On those airplanes in which P/N 0850404-1 boost pump relay is installed, relocate this relay to wing trailing edge per Cessna Service Kit SK 310-90. (This relay is no longer eligible for installation in the wing leading edge. b) P/N FC 215-136 boost pump relay already installed in the wing leading edge is acceptable and as an alternative to Paragraph a), P/N 0850404-1 boost pump relay may be replaced with P/N FC 215-136 boost pump relay installed in the present wing leading edge location. c) On all airplanes relocate the boost pump resistor in accordance with Cessna Service Kit SK 310-90. 5) Place amended checklist entitled "Aircraft Fire Procedures Checklist" in the cockpit. This checklist is supplied with Cessna Service Kit SK 310-90. This amendment becomes effective April 6, 1973.
2005-14-06: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 707-300B, -300C, and -400 series airplanes. This AD requires repetitive inspections to detect cracked or broken hinge fitting assemblies of the inboard leading edge slats, and corrective action if necessary. This AD also provides as an option a preventive modification, which defers the repetitive inspections. In addition, this AD provides an option of replacing all hinge fitting assemblies with new, improved parts, which terminates the repetitive inspection requirements. This AD is prompted by results of a review to identify and implement procedures to ensure the continued structural airworthiness of aging transport category airplanes. We are issuing this AD to detect and correct fatigue cracking of the hinge fitting assembly of the inboard leading edge slats, which could result in reduced structural integrity of the slat system. This condition could result in loss of the inboard leading edge slat andcould cause the flightcrew to lose control of the airplane.
88-10-01: 88-10-01 BEECH: Amendment 39-5904. Applies to Models A23-24 and A24 (Serial Numbers (S/Ns) MA-1 through MA-368); Model A24R (S/Ns MC-2 through MC-95); Models A24R, B24R, and C24R (S/Ns MC-96 through MC-795), airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent reduction or loss of engine power due to fuel flow blockage resulting from broken electric fuel boost pump vanes in the engine driven fuel pump, accomplish the following: (a) For airplanes with 14 volt electrical systems, replace the existing electric fuel boost pump with a Beech P/N 1816-00-1 pump in accordance with the instructions in Beech Service Bulletin (MSB) No. 2217, dated February 1988. (b) For airplanes with 28 volt electrical systems, replace the existing electric fuel boost pump with a Beech P/N 1817-00-1 pump in accordance with the instructions in Beech MSB No. 2217,dated February 1988. (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, Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Department 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on June 6, 1988.
75-22-13: 75-22-13 LITTON SYSTEMS, INC., AERO PRODUCTS DIVISION: Amendment 39-2404. Applies to all LTN-72 inertial navigation systems installed on various airplane models, certificated in all categories, including, but not limited to, McDonnell Douglas DC-8 and DC-10 airplanes and Boeing 707 and 747 airplanes. \n\n\tCompliance required as indicated prior to January 1, 1976 unless already accomplished. \n\n\tTo provide the required failure warning indication of power loss, accomplish Litton Service Bulletin No. 34-72-80, dated February 20, 1975, or later FAA-approved revision, or an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective December 1, 1975.
2005-12-51: The FAA is adopting a new airworthiness directive (AD) for Rockwell International (Aircraft Specification No. A-2-575 previously held by North American and recently purchased by Boeing) Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, SNJ-7, and T-6G airplanes; and Autair Ltd. (Aircraft Specification No. AR-11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT-16) airplanes. This AD contains the same information as emergency AD 2005-12-51 and publishes the action in the Federal Register. It requires immediate and repetitive inspections of the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of both wings for fatigue cracks; and, if any crack is found, replacement of the cracked angle with a new angle. This AD is the result of a report of a Rockwell International Model SNJ-6 (AT-6F) airplane crash that occurred on May 9, 2005, resulting in two fatalities. We are issuing this AD todetect and correct any fatigue crack in the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of either wing, which could result in failure of the wing. This failure could lead to loss of control of the aircraft.
97-05-11 R1: This amendment revises an existing airworthiness directive (AD), applicable to AlliedSignal Inc. ALF502 and LF507 series turbofan engines, that currently requires initial and repetitive inspections of the oil system chip detectors and oil filter bypass valve, and optional installation of an improved oil filter bypass valve, to ensure the integrity of the reduction gear system and overspeed protection system. This amendment adds an initial inspection threshold for the oil maintenance requirements that was inadvertently omitted from AD 97-05-11, and makes editorial corrections. Paragraphs (b) through (f) of AD 97-05-11 have been rearranged in this AD to make these corrections. This amendment is prompted by the inadvertent omission of the initial inspection threshold. The actions specified by this AD are intended to prevent No. 4 and 5 duplex bearing failure, which can result in a Stage 4 low pressure turbine (LPT) rotor failure, an uncontained engine failure, and damage tothe aircraft.