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2009-03-03: We are adopting a new airworthiness directive (AD) for certain McDonnell Douglas airplanes listed above. This AD requires installing a dam assembly for the container of the fuel boost pump of the center tank located in the right main tank, and doing the related investigative actions, and corrective actions if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the center tank fuel boost pump from operating in a fuel vapor zone and becoming a potential ignition source in the right main tank, potentially resulting in a fuel tank explosion and consequent loss of the airplane.
73-20-07 R2: 73-20-07 R2 BEECH: Amendment 39-1728 as amended by Amendment 39-3732 is further amended by Amendment 39-4461. Applies to Models A23-19, 19A, M19A, B-19 (Serial Numbers MB-1 through MB-708); Models 23, A23, A23A, B23, C23 (Serial Numbers M-1 through M-1576); Models A23-24, A24 (Serial Numbers MA-1 through MA-368); and Models A24R, B24R (Serial Numbers MC-2 through MC-282) certified in all categories. Compliance: Required as indicated. To detect cracks or other structural damage to the forward wing attach point brackets (P/N 169-400013-3 and -5(LH) and 169-400013-4 and -6 (RH)), within the next 25 hours' time in service after the effective date of this AD unless previously accomplished on airplanes having more than 100 hours' time in service and thereafter at each normal annual, progressive or 100 hour inspection interval as required by FAR 91.169, accomplish the following: (a) Remove the seats and sidepanels and visually inspect the forward wing attach brackets, P/N169-400013-3 and -5 (LH) and 169-400013-4 and -6 (RH), to determine if cracks or other structural damage exists in the area around the attach bolt hole. This inspection is to be performed in accordance with Beech Service Instructions 0042-031, Rev. II. (b) If as a result of any inspection required herein cracks or other structural damage is discovered, prior to further flight repair the forward wing attach brackets in accordance with Beechcraft Service Instructions 0042-031, or later FAA-approved revisions, or any other repair approved by the Chief, Wichita Aircraft Certification Office, FAA, Wichita, Kansas. To accomplish the repair required herein the aircraft may be flown in accordance with FAR 21.197 to a base where the repair may be performed. (c) The inspection intervals required in this AD may be adjusted 15 plus or minus hours where required to fit users maintenance cycles if authorized by an FAA Flight Standards Inspector. (d) When airplanes have been modified by installing all of the new wing attach structural parts listed under materials in Beechcraft Service Instructions No. 0042-031, Rev. II, further compliance with this AD is not required. (e) Any equivalent method of compliance with this AD must be approved by the Chief, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. Amendment 39-1728 became effective October 5, 1973. Amendment 39-3732 became effective March 21, 1980. This Amendment 39-4461 became effective on September 3, 1982.
92-16-19: 92-16-19 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-8329. Docket No. 92-NM-125-AD. Supersedes AD 92-10-51, Amendment 39-8271. Applicability: All Model L-1011-385 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent degradation of airplane pitch control, accomplish the following: (a) Prior to the accumulation of 12,000 landings, or within 3 days after June 24, 1992 (the effective date of AD 92-10-51, Amendment 39-8271), whichever occurs later, accomplish the procedures specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD: (1) Gain access to the lower end of the stabilizer hydraulic actuators (four per airplane) where they attach to the front spar of the horizontal stabilizer center box structure at Fuselage Station FS 1875. (2) Inspect for missing, sheared, or deformed stabilizer lower actuator attach pins, part number 1563117-101 (one per actuator). (3)If any pin is missing, sheared, or deformed, replace the pin prior to further flight. (b) At the applicable time specified in paragraph (b)(1), (b)(2), or (b)(3) of this AD, either perform a one-time magnetic particle inspection to detect cracks on each of the four lower horizontal stabilizer actuator pins (part number 1563117-101), or replace each of the four actuator pins (part number 1563117-101) with a new pin, in accordance with Lockheed Service Bulletin 093-27-304, Revision 1, dated May 28, 1992. (1) For airplanes that have accumulated less than 12,000 landings as of the effective date of this AD: Prior to the accumulation of 12,000 landings, or within 60 days after the effective date of this AD, whichever occurs later. (2) For airplanes that have accumulated at least 12,000 landings but not more than 20,000 landings as of the effective date of this AD: Within 45 days after the effective date of this AD. (3) For airplanes that have accumulated more than20,000 landings as of the effective date of this AD: Within 30 days after the effective date of this AD. (c) If a magnetic particle inspection is performed in accordance with paragraph (b) of this AD, accomplish the procedures specified in paragraph (c)(1) or (c)(2), as applicable: (1) If any actuator pin is found to be cracked: Prior to further flight, replace the cracked pin with a new pin, in accordance with Lockheed Service Bulletin 093-27-304, Revision 1, dated May 28, 1992. Thereafter, prior to the accumulation of 12,000 landings on each actuator pin, part number 1563117-101, it must be replaced with a new pin. (2) If no actuator pins are found to be cracked: Prior to the accumulation of 1,000 landings after accomplishing the magnetic particle inspection, replace the pin with a new pin, in accordance with Lockheed Service Bulletin 093-27-304, Revision 1, dated May 28, 1992. Thereafter, prior to the accumulation of 12,000 landings on each actuator pin, part number 1563117-101, it must be replaced with a new pin. (d) If each of the four actuator pins, part number 1563117-101, are replaced with a new pin in accordance with paragraph (b) of this AD: Thereafter, prior to the accumulation of 12,000 landings on each actuator pin, it must be replaced with a new pin. (e) 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 (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a locationwhere the requirements of this AD can be accomplished. (g) The inspection and replacement shall be done in accordance with Lockheed Service Bulletin 093-27-304, Revision 1, dated May 28, 1992, which contains the following list of effective pages: Page Number Revision Level Date 1 - 8 1 May 28, 1992 9 - 11 Original May 15, 1992 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Lockheed Western Export Company (LWEC), Dept. 693, Zone 0755, 86 South Cobb Drive, Marietta, Georgia 30063. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the FAA, Atlanta Aircraft Certification Office, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street NW., 7th Floor, Suite 700, Washington, DC. (h) This amendment becomes effectiveon September 1, 1992.
2000-24-24: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls- Royce plc RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 series turbofan engines having common nozzle assembly part number (P/N) FK16544 or FK16558. This action requires initial and repetitive visual inspections of the inner and outer skins of the common nozzle assembly and specifies allowable limits for cracks, loose rivets, and missing rivets. This action also requires repair if the common nozzle assembly damage exceeds allowable limits. This amendment is prompted by two reports of in-flight inner skin detachment. The actions specified in this AD are intended to detect cracks, loose rivets, and missing rivets, which could result in inner skin detachment, release of common nozzle assembly debris from the engine, and possible damage to the airplane control surfaces.
89-03-06: 89-03-06 FOKKER: Amendment 39-6122. Applicability: Model F-27 series airplanes, Serial Numbers 10623 through 10692, in Mark 500 configuration, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of electrical power and eliminate a potential fire hazard, due to chafing wire bundles, accomplish the following: A. Within 60 days after the effective date of this AD, perform a one-time inspection of the upper fuselage cableloom for chafing and insufficient clamping, and repair, if necessary, in accordance with Fokker Service Bulletin F27/24-77, dated June 7, 1988. B. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. C. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6122, AD 89-03-06) becomes effective March 6, 1989.
2022-23-10: The FAA is superseding Airworthiness Directive (AD) 2021-06- 03, which applied to all The Boeing Company Model 777F series airplanes. AD 2021-06-03 required deactivating the potable water system. This AD was prompted by a report of a water supply line that detached at a certain joint located above an electronic equipment (EE) cooling filter, leading to water intrusion into the forward EE bay. This AD retains the actions required by AD 2021-06-03 and requires installing a shroud to the water supply line in the forward cargo compartment, and performing a leak test of the potable water system. For certain airplanes, this AD also requires replacing tubes and hoses from the water supply line and installing a shroud to the water return line. The FAA is issuing this AD to address the unsafe condition on these products.
2010-21-13: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installing a support bracket and coupler on the left and right wing-to-fuselage transition, and metallic overbraid on the left and right leading edge wire assembly. This AD was prompted by fuel system reviews conducted by the manufacturer, as well as reports that the fuel quantity system was affected by lightning-induced transients. We are issuing this AD to prevent lightning-induced transients to the fuel quantity indication system, which could cause voltage levels to go beyond original design levels between fuel tank probes and structure, and become a potential ignition source at the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
83-04-02: 83-04-02 FOKKER-VFW B.V.: Amendment 39-4569. Applies to Model F28 airplanes serial number 11003 and on. To prevent loss of aileron control, accomplish the following, unless already accomplished within the last three months prior to the effective date of this AD: 1. Within the next 50 hours time in service or one month, whichever occurs first after the effective date of this AD, perform a one time inspection of the aileron control cables in both the R.H. and L.H. wings for airplanes with more than one year's time from the date of manufacture in accordance with the following instructions: a. Open the main landing gear doors and flap shroud doors 81j, 81k, 82j, and 82k. b. Rotate the aileron control wheel in the cockpit to the full left-hand position. c. With the control wheel in this position, inspect the four aileron input cables at location of cable pulleys between stations 3100 and 3600 (illustrated parts catalog, chapter 27-10-01-05). Inspection must be performed with the aid of a mirror and a very strong light otherwise corrosion may remain undetected. d. If wires are broken or there are definite signs of corrosion in the cables, accomplish the actions of paragraph 2. e. Rotate the aileron control wheel in the cockpit to the full right-hand position and repeat the inspections described in paragraphs (c) and (d). 2. If corrosion on the cables is evident from the inspections of paragraph 1, above, accomplish the following: a. Disconnect the cable at the turnbuckle in the wheelwell per the F28 Maintenance Manual, chapter 27-11. b. Pull out the cable at the cable pulleys between stations 3100 and 3600. c. Carefully bend the cable one time at the location of the corrosion over a radius of one inch. If any wire breaks while being bent, replace the cable prior to further flight. d. If no wires failed during the bending test of paragraph 2(c), repeat the test by bending the cable in the opposite direction. If any wire breaks, replace the cable before further flight. e. If the cable is not rejected by the bending tests of paragraphs 2(c) or 2(d), inspect the cable for interior corrosion in accordance with the F28 Maintenance Manual, chapter 20-30-9. f. If interior corrosion is found, replace the cable before further flight. g. Remove any exterior corrosion and treat the cable in accordance with F28 Maintenance Manual, Chapter 20-30-9. h. Reconnect the turnbuckles in the L.H. and R.H. wheelwells and adjust the cable system in accordance with F28 Maintenance Manual, Chapter 27-11-00, and check the aileron for free and smooth operation. 3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 4. Special 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. The 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). This amendment becomes effective March 7, 1983.
2000-15-52: This document publishes in the Federal Register an amendment adopting superseding Airworthiness Directive (AD) 2000-15-52, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. Model (BHTI) Model 204B, 205A, 205A-1, 205B, and 212 helicopters by individual letters. This AD reduces the retirement index number (RIN) life limit for the main rotor mast (mast); increases the RIN factor for masts and main rotor trunnions (trunnions); applies standard RIN factors for all external load lifts; and requires a one-time inspection of the snap ring groove area of the mast. This AD also establishes RIN factors for masts and trunnions that have been previously installed on military or restricted category helicopters and removes from service those masts that have been previously installed with a hub spring. This amendment is prompted by an occurrence of a cracked mast at a lower value than the established RIN life limit. The actions specified by thisAD are intended to preclude the occurrence of fatigue cracks in the damper clamp splined area of a mast. A crack in the damper clamp splined area could result in failure of a mast or trunnion, separation of the main rotor system, and subsequent loss of control of the helicopter.
2016-05-01: We are superseding Airworthiness Directive (AD) 96-12-12, which applies to certain Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes. AD 96-12-12 requires a one-time inspection of the bulkhead assembly at fuselage station (FS) 317.75 for cracks and the installation of one of two reinforcement kits determined by whether cracks were found during the inspection. This new AD requires repetitive inspections of the bulkhead assembly at FS 317.75 for cracks, repair of cracks as necessary, and the installation of a reinforcement modification. This AD was prompted by cracks found in the FS 317.75 upper bulkhead. We are issuing this AD to correct the unsafe condition on these products.