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86-07-10: 86-07-10 BOEING: Amendment 39-5284. Applies to all Model 767 airplanes, certificated in any category, equipped with slide packboard Part Number 416T2003-14 or slide/raft packboard Part Number 416T2003-15. To ensure that the escape slide release mechanism operates properly, accomplish the following, unless already accomplished: \n\n\tA.\tAccomplish the inspection, test, and modification procedures in accordance with Boeing Service Bulletin 767-25-A0071, dated September 27, 1985, or later FAA-approved revisions, as follows: \n\n\t\t1.\tFor packboards that have been in service over twenty-one months on the effective date of this AD, accomplish the inspection and modification within the next three months after the effective date of this AD. \n\n\t\t2.\tFor all other packboards, accomplish the inspection and modification prior to the accumulation of twenty-four months in service. \n\n\tB.\tAll packboards must meet the test requirements of Boeing Service Bulletin 767- 25-A0071, Part III.C., Figure 1, circle Note 4, after modification. Packboards not meeting these requirements must not be placed in service. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this proposal who have not already received the appropriate service document from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective May 16, 1986.
88-03-07: 88-03-07 CESSNA: Amendment 39-5841. Applies to Cessna Models 340, 340A (Serial Numbers 340-0001 thru 340A1817) and 414 (Serial Numbers 414-0001 thru 414-0965) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To detect and correct fuel line chafing or fuel leaks behind the engine firewall, accomplish the following: (a) Remove both firewall access covers and inspect the crossfed fuel lines for evidence of chafing in accordance with Cessna Service Bulletin No. MEB87-7, Revision 1, dated January 8, 1988. (b) If, as a result of the inspection required by paragraph (a), evidence of chafing is found that exceeds the criteria specified in Cessna Service Bulletin, No. MEB 87-7, Revision 1, dated January 8, 1988, prior to further flight, replace the affected line with an airworthy part. (c) In addition to the inspection required in paragraph (a), modify the firewall stiffener flanges and fuel lines in accordance with Cessna Service bulletin No. MEB87-7, Revision 1, dated January 8, 1988. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, 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 Cessna Aircraft Company, Customer Service, P.O. Box 7704, Wichita, Kansas 67277; or may examine the document(s) at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment 39-5841 supersedes AD 87-23-11, Amendment 39-5782, published in the Federal Register on November 30, 1987, (52 FR 45451). This amendment 39-5841 becomes effective on February 10, 1988.
97-15-01: 97-15-01 Teledyne Continental Motors: Priority Letter issued on July 17, 1997. Docket No. 97-ANE-34-AD. Applicability: Teledyne Continental Motors (TCM) new and rebuilt Model O-470 and IO-470 series engines with serial numbers (S/Ns) listed in Table 1 of TCM Critical Service Bulletin (CSB) No. CSB97-10, dated June 19, 1997; and TCM Model E-165, E-185, E-225, O-470 and IO-470 series engines, regardless of S/N, which have cylinder(s) with part number and purchase date as shown in Table 2 of TCM CSB No. CSB97-10, dated June 19, 1997. These engines are installed on but not limited to the following aircraft: Bellanca Models 14-19-2 and 14-19-3; Cessna Models 180, 180A through K, 182, 182A through R, 185, 185A through E, 188, 188A, 188B, 210, 210A through C, 210-5 (205), 210-5A (205A), 305A, 305C, 305D, 305F, 310, 310A through Q, E310H, E310J, 310J-1; Frontier-Aerospace, Inc. (Fletcher) Models FU-24 and FU-24A; Luscombe Aircraft Corporation Model 11A; Navion models Navion, NavionA, and Navion D through G; Prop-Jets, Inc. Models 200, 200A through C; Raytheon (formerly Beech) Models 35, A35 through P35, 35R, 35-33, 35-A355, 35-B33, 35-C33, E33, F33, 45 (YT-34), A45 (T-34A, B-45), D45(T-34B), 95-55, 95-55A, 95-B55, 95-B55A and 95-B55B; Reims models F182P and F182Q; and Twin Commander Aircraft, Inc. Model 500-A. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent extreme side loading of the piston, and consequent failure of the piston and engine, accomplish the following: (a) For the TCM O-470 and IO-470 series engines listed by S/N in Table 1 of TCM CSB No. CSB97-10 dated June 19, 1997, within 10 hours time in service (TIS) after receipt of this priority letter AD, accomplish the following: (1) Remove from service the cylinders, six each, and the piston pins, six each, in accordance with the Inspection Instructions, Part 2A, and Appendix A of TCM CSB No. CSB97-10, dated June 19, 1997. (2) Obtain serviceable replacement parts and reassemble the engine in accordance with the Inspection Instructions, Part 2B, of TCM CSB No. CSB97-10, dated June 19, 1997. (b) For the E-165, E-185, E-225, series engines and those O-470 and IO-470 series engines not listed by S/N in Table 1 of TCM CSB No. CSB97-10 dated June 19, 1997, within 10 hours TIS after receipt of this priority letter AD, accomplish the following: (1) Determine from engine log books or maintenance records if a cylinder has been replaced with a cylinder purchased in the time frames shown in Table 2 of TCM CSB No. CSB97-10, dated June 19, 1997. (2) If a cylinder was not replaced with a cylinder purchased during those time frames listed in the CSB, or if a cylinder is identified with the letter "M" or "P" steel stamped after the cylinder position number, as cylinders marked with "M" or "P" have a surface finish that has been found to be within specification, no further action is required. The cylinder position number is located at the 12 o'clock position on the cylinder mounting flange. (3) If a cylinder has been replaced with a cylinder purchased during those time frames listed in the CSB, remove from service the affected cylinders and piston pins in accordancewith the Inspection Instructions, Part 2A, and Appendix A of TCM CSB No. CSB97-10, dated June 19, 1997. (4) Obtain serviceable replacement parts and reassemble the engine in accordance with the Inspection Instructions, Part 2B, of TCM CSB No. CSB97-10, dated June 19, 1997. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Atlanta Aircraft Certification Office. Operators shall submit their requests through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Atlanta Aircraft Certification Office. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (e) Copies of the applicable service information may be obtained from Teledyne Continental Motors, P.O. Box 90, Mobile, AL 36601; telephone (334) 438-3411. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA. (f) Priority Letter AD 97-15-01, issued July 17, 1997, becomes effective upon receipt.
89-14-09: 89-14-09 EMPRESA BRASILEIRA DE AERONAUTICA, S.A. (EMBRAER): Amendment 39-6258. Applicability: EMBRAER Model EMB-120 and EMB-120RT series airplanes, equipped with Garrett auxiliary power units (APU) models GTCP36-150(A) or GTCP36-150(AA), certificated in any category. Compliance: Required within 25 hours time in service, or prior to the next APU start, whichever occurs later, after the effective date of this AD, unless previously accomplished. To prevent an uncontrolled APU overspeed, accomplish the following: A. Inspect the APU electrical control unit (ECU), Part No. 2118052-1/2118596-2, for water contamination, as follows: 1. Gain access to and remove the APU ECU from the airplane. 2. Install plastic covers on J1 and J2 connectors on the ECU. 3. In a suitable workshop area, cut the two tamper proof seals along the box/lid split line. 4. Remove the 14 screws that secure the ECU lid to the box. 5. Remove the ECU lid. 6. Use special attention to ensure that no foreign objects or material are allowed to enter the ECU, and that nothing inside the ECU is either touched or removed. 7. Using a bright light, inspect inside the ECU for moisture or water. 8. Turn the ECU slowly upside down and determine if water can be drained from the ECU. 9. If water is seen inside the ECU or if water can be drained out of the ECU, remove the ECU from service and replace it with a serviceable unit. 10. If the inside of the ECU is dry, carefully realign the ECU lid and packing with ECU box, and reinstall the 14 screws using an alternating fashion around the circumference until there is metal to metal contact between the ECU lid and the ECU box around the entire circumference. 11. Have a Quality Assurance person re-seal the ECU using new tamper- proof seals. 12. Reinstall the ECU. B. Prior to pressurized cleaning, install a suitable cover over the vent screen, to prevent exposing the APU ECU area to water contamination. Remove this temporary cover following completion of the pressurized cleaning procedure. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Atlanta Aircraft Certification Office. D. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to EMBRAER, 276 S.W. 34th Street, Fort Lauderdale, Florida 33315. These documents may be examined at the FAA Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia. This amendment (39-6258, AD 89-14-09) becomes effective on July 18, 1989.
46-01-02: 46-01-02 CESSNA: (Was Service Note 2 of AD-722-5.) Applies to All T-50 Aircraft. When airplane has been subjected to a hailstorm, a careful inspection should be made for damage to plywood reinforcements under fabric covering, even when hail has not caused apparent damage. (Cessna Service Bulletin No. 101 dated July 19, 1945, also covers this subject.)
99-10-04: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires modification of the pulley assemblies of the elevator and rudder control cables on the rear pressure bulkhead. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the pulley assemblies of the elevator and rudder control cables in the event of an elevator or rudder control cable jam, which could result in reduced controllability of the airplane.
2019-06-01: We are superseding Airworthiness Directive (AD) 2018-24-01 for certain International Aero Engines (IAE) PW1133G-JM, PW1133GA-JM, PW1130G-JM, PW1127G-JM, PW1127GA-JM, PW1127G1-JM, PW1124G-JM, PW1124G1- JM, and PW1122G-JM turbofan engines. AD 2018-24-01 required removing certain low-pressure turbine (LPT) 1st- and 3rd-stage disks from service and replacing with a part eligible for installation. This AD retains the same requirements as AD 2018-24-01. This AD was prompted by the discovery of incorrect serial numbers in the identification of LPT disks in AD 2018-24-01. We are issuing this AD to address the unsafe condition on these products.
98-15-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-15-51 that was sent previously to all known U.S. owners and operators of all Airbus Model A319, A320, A321, A300, A310, A300-600, A330, and A340 series airplanes by individual telegrams. This AD requires an initial and repetitive in-flight operational checks of the alternate braking system, and replacement of the braking dual distribution valve (BDDV) with a serviceable part, if necessary. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the alternate braking system, which could result in the airplane overrunning the end of the runway during landing.
2006-16-11: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-700 and 737-800 series airplanes. This AD requires performing a one-time high frequency eddy current inspection for cracking of the backup intercostals located above the cutout for the forward airstair door; doing related investigative and corrective actions if any crack is found; and doing other specified corrective actions if no crack is found. This AD results from a report of fatigue cracks discovered during a full-scale fatigue test conducted by the manufacturer. We are issuing this AD to detect and correct such cracking, which could result in more extensive fatigue cracking and lead to possible loss of cabin pressure.
2006-16-09: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model MD-90-30 airplanes. This AD requires installing a clamp, bonding jumper assembly, and attaching hardware to the refueling manifold in the right wing refueling station area. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent arcing on the in-tank side of the fueling valve during a lightning strike, which could result in an ignition source that could ignite fuel vapor and cause a fuel tank explosion.