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76-19-03: 76-19-03 HUGHES HELICOPTERS: Amendment 39-2725. Applies to Hughes Model 369H, 369HS, 369HE and 369HM helicopters, certificated in all categories, equipped with shock mounted stabilizer strut assembly P/N 369A2001-601. Compliance required as indicated unless already accomplished. To prevent fatigue failures of the damper plunger which could result in the loss of the stabilizer strut and possible contact with the tail rotor, accomplish the following: (a) Within 25 hours time in service after the effective date of this AD, disassemble the stabilizer strut P/N 369A2001-601 and determine if the damper plunger P/N 369A2130 or P/N 369A2130-3 has cut threads in accordance with Hughes Service Information Notice HN102.1 dated August 25, 1976 or later FAA-approved revision. (b) If the damper plunger is found to have cut threads during the inspection required by paragraph (a), before further flight, either replace the damper plunger with a damper plunger with rolled threads, or inspect the threaded area for cracks using the dye penetrant or magnetic particle inspection method. (1) If cracks are found, before further flight, replace the damper plunger with a damper plunger, P/N 369A2130 or P/N 369A2130-3, with rolled threads. (2) If cracks are not found, within 100 hours additional time in service after the inspection required by paragraph (a), replace the damper plunger with a damper plunger, P/N 369A2130 or P/N 369A2130-3, with rolled threads. (c) Equivalent inspection methods or alternate replacement parts may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate helicopters to a base for the accomplishment of the inspections required by this AD. This amendment becomes effective September 24, 1976.
91-03-12: 91-03-12 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-6856. Docket No. 90-ASW-3. Applicability: All Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters equipped with emergency float bags, part numbers (P/N) 206-050-248-107, -109 and -111 manufactured prior to September 1, 1989. These float bags are used in BHTI emergency float kits 206-706-210 and 206-706-211. Compliance: Required within the next 100 hours' time in service after the effective date of this AD or upon installation of float bags from spares, unless already accomplished. To prevent unequal float inflation which could result in aircraft rollover and impede emergency egress after an emergency water landing, accomplish the following: (a) Inspect each float bag to determine if any square body, brass type inflation valves, P/N 222-336-101-19 or -23, are installed. If any of these valves are found, install an appropriate flow restrictor in accordance with the instructions in Appendix I of this AD for Models 206A and B, or Appendix II of this AD for Models 206L, L-1 and L-3, as applicable. (b) An alternative method of compliance, which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, ASW-170, FAA Southwest Region, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. (c) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the requirements of this AD may be accomplished. NOTE: Appendix I, which is not reprinted in this AD, includes material from Bell Helicopter Textron, Inc., (BHTI) Alert Service Bulletin No. 206-89-49, and Appendix II, which is not reprinted in this AD, includes material from BHTI Alert Service Bulletin No. 206L-89-63, both dated October 10, 1989. A copy of the service bulletins may be obtained from BHTI, P.O. Box 482, Fort Worth, Texas 76101. This amendment (39-6856, AD 91-03-12) becomes effective on February 28, 1991.
2005-17-09: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747, 757, 767, and 777 series airplanes. That AD currently requires modifying certain drip shields located on the flight deck, and follow-on actions. This new AD removes certain airplanes that are included in the applicability statement of the existing AD, and requires modifying additional drip shields on the flight deck of certain other airplanes. This AD is prompted by a determination that certain airplanes have drip shields that are not adequately resistant to fire. We are issuing this AD to prevent potential ignition of the moisture barrier cover of the drip shield, which could propagate a small fire that results from an electrical arc, leading to a larger fire. \n\nDATES: This AD becomes effective September 27, 2005. \n\n\tThe incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of September 27, 2005.On February 2, 2001 (65 FR 82901, December 29, 2000), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD.
2001-23-12 R1: This document revises an existing airworthiness directive (AD) that applies to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. That AD currently requires a one-time review of records to determine whether an airplane has been repainted since its delivery from the factory; and a one-time inspection to detect damage associated with improper preparation for the repainting, and corrective action if necessary. The actions specified in that AD are intended to detect and correct damage to the aluminum skin of the airplane, which could result in a weakening of the structure of the airplane. This document corrects certain conditional requirements of the existing AD. The incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of December 31, 2001 (66 FR 58927, November 26, 2001).
2005-17-03: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires installing additional shielding of the hydraulic lines in the wing box area. This AD results from the determination that the additional hydraulic line shields will protect the lines from possible impact by tire debris if the tire tread fails. We are issuing this AD to prevent damage to the hydraulic lines and subsequent leakage from the two hydraulic systems, which could result in loss of braking capability on the affected side of the airplane, asymmetrical braking, and reduced directional control--particularly during a rejected takeoff.
76-19-01: 76-19-01 BRITISH AIRCRAFT CORPORATION: Amendment 39-2723. Applies to Viscount Model 744, 745D, and 810 Series airplanes, certificated in all categories. Compliance is required as indicated. To prevent possible failure of the elevator spring servo tab control mechanism, accomplish the following: (a) Replace the spigot bracket, P/N 70120-367, that attaches the elevator spring tab system bellcrank to the left elevator torque tube with a new bracket of the same part number as follows: (1) If neither paragraph (b) or (c) of AD 71-4-2 has been complied with prior to the effective date of this AD, replace the bracket within the next 100 hours time in service after the effective date of this AD or prior to the accumulation of 12,000 hours total time in service on the bracket, whichever occurs later. (2) If paragraph (b) or (c) of AD 71-4-2 has been complied with prior to the effective date of this AD, replace the bracket at the latest of the following:(i) Within the next 50 hours time in service after the effective date of this AD. (ii) Within 1000 hours time in service after complying with AD 71-4-2 if the bracket was not replaced in complying with that AD. (iii) Prior to the accumulation of 12,000 hours total time in service on the bracket. (3) After complying with paragraph (a)(1) or (a)(2) of this AD, as appropriate, continue to replace the brackets prior to the accumulation of 12,000 hours total time in service after installation. (b) Operators who have not kept records of total hours time in service on individual spigot brackets, P/N 70120-367, must substitute in lieu thereof the total hours time in service of the airplane. This supersedes Amendment 39-1154 (36 FR 2562), AD 71-4-2. This amendment becomes effective October 15, 1976.
2005-17-02: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires inspecting the valve control and indication wire bundles of the fuel system of the wing rear spar for discrepancies, and corrective action if necessary. This AD is prompted by reports of six incidents of the wire bundles chafing against the rear spar stiffeners outside the fuel tank. We are issuing this AD to prevent this chafing, which could result in wire damage leading to a short circuit, subsequent ignition of flammable vapors, and possible uncontrollable fire during fueling or flight.
97-19-12: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A,-11, -15, -17, and -17R series turbofan engines, that requires initial and repetitive fluorescent penetrant and eddy current inspections of 4th stage low pressure turbine (LPT) hubs for cracks, and, if necessary, replacement with serviceable parts. This amendment is prompted by a report of an uncontained 4th stage LPT blade release. The actions specified by this AD are intended to prevent a 4th stage LPT blade release due to hub cracking, which can result in an uncontained engine failure and damage to the aircraft.
97-19-06: This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Sikorsky Aircraft Corporation Model S-61A, D, E, L, N, NM, R, and V helicopters, that currently requires inspecting certain main rotor blade assemblies (blades) to determine if a blade has a blade trailing edge pocket assembly (pocket assembly) that was anodized by Poly-Metal Company during a specified time period, and if so, replacing it with an airworthy blade. This amendment requires the same actions as the existing AD, but corrects two serial numbers in the list of the applicable blades. This amendment is prompted by the manufacturer's issuance of a service bulletin with a revised list of blade serial numbers. The actions specified by this AD are intended to prevent disbonding and separation of portions of the blade, subsequent excessive vibrations, and loss of control of the helicopter.
78-08-05: 78-08-05 MCDONNELL DOUGLAS: Amendment 39-3184. Applies to DC-10-10, -10F, -30, -30F and -40 Series airplanes certificated in all categories, that are equipped with Litton -51 or Litton -72 Inertial Navigation Systems or Litton -58 Inertial Sensor Systems. Airplanes which are equipped with these Litton inertial systems after the effective date of this AD must be modified as defined herein prior to installation of the inertial systems. \n\n\tCompliance is required as indicated unless already accomplished. \n\n\tTo prevent simultaneous loss of primary attitude and heading information during takeoff roll and subsequent flight accomplish the following: \n\n\t(a)\tOn or before July 31, 1979 unless already accomplished, or unless incorporated in production, modify the airplane's navigation rack in accordance with McDonnell Douglas DC-10 Service Bulletin 25-251 dated August 26, 1977, or later FAA approved revisions. \n\n\t(b)\tEquivalent modifications, procedures, or revisions may be used whenapproved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to a base for accomplishment of the modification required by this AD. \n\n\tThis amendment becomes effective May 16, 1978.