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90-17-09: 90-17-09 BRITISH AEROSPACE: Amendment 39-6693. Docket No. 90-NM-53-AD. Applicability: Model BAC 1-11 200 and 400 series airplanes, as listed in British Aerospace Alert Service Bulletin 27-A-PM587l, Issue No. 1, dated October 4, 1989, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a reduction in airplane stability and controllability, accomplish the following: A. Within 60 days after the effective date of this AD, unless accomplished within the last 12 months, and thereafter at intervals not to exceed 18 months, perform a visual inspection of both elevator lower control levers, in accordance with paragraphs 2.1 and 2.3 through 2.9 of British Aerospace Alert Service Bulletin 27-A-PM5871, Issue No. 1, dated October 4, 1989. B. If cracks are found, prior to further flight, replace the elevator control lever(s) in accordance with the British Aerospace Alert Service Bulletin 27-A-PM5871, Issue No.1, dated October 4, 1989. C. Replacement of both elevator lower control levers with levers manufactured from L64 or L99 material constitutes terminating action for repetitive inspections required by paragraph A. of this AD. D. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. E. 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 British Aerospace, PLC, Librarian for Service Bulletins, P. O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington. This amendment (39-6693, AD 90-17-09) becomes effective on September 17, 1990.
2015-17-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Pratt and Whitney engines. This AD was prompted by reports of blocked drain lines at the engine forward strut that caused flammable fluid to accumulate in a flammable leakage zone. This AD requires repetitive functional checks for blockage of the forward strut drain line and doing corrective actions if necessary, and a one-time cleaning of certain forward strut drain lines. This AD also provides an optional replacement of the drain lines and installation of insulation blankets, and a revision of the maintenance or inspection program, as applicable, to incorporate a certain airworthiness limitation, which would terminate the repetitive checks of the forward strut drain line. We are issuing this AD to detect and correct blockage of forward strut drain lines, which could cause flammable fluids to collect in the \n\n((Page 52949)) \n\nforward strut area and potentially cause an uncontrolled fire or cause failure of engine attachment structure and consequent airplane loss.
87-17-02: 87-17-02 BOEING: Amendment 39-5703. Applies to Model 767 series airplanes specified in Boeing Alert Service Bulletin 767-24A0039, dated March 12, 1987, certificated in any category. Compliance is required as indicated unless previously accomplished. \n\n\tTo minimize the fire hazard associated with overheating of the transformer rectifier unit (TRU) of the auxiliary power unit (APU) starter motor, accomplish the following within 3 months after the effective date of this AD: \n\n\tA.\tReplace the 50-ampere circuit breaker used for the APU starter TRU with a 35- ampere circuit breaker in accordance with Boeing Service Bulletin 767-24A0039, dated March 12, 1987, or later FAA-approved revision. \n\n\tB.\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\tC.\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 the modification required by this AD. \n\tAll persons affected by this directive who have not already received copies of 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 September 13, 1987.
96-12-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires reinforcing the lower right-hand wing skin at the fueling adapter. This amendment is prompted by results of tests, which revealed that fatigue cracks can develop in the lower right-hand wing skin at the attachment bolt holes of the fueling adapter. The actions specified by this AD are intended to prevent reduced structural capability of the wing and fuel leakage.
77-16-08: 77-16-08 EIRIAVION OY (FORMERLY MOLINO OY): Amendment 39-3005. Applies to Model PIK-20D sailplanes with serial numbers 20510 through 20532, 20534 through 20540, 20542 through 20544, 20546, 20548, 20552, 20555, and 20556. To prevent separation of wing upper panel spar cap and wing main spar shear web, before further flight, unless already accomplished, comply with paragraph (a), (b), or (c). (a) Replace wing panels with new wing panels identified by the manufacturer as serviceable replacements. (b) Repair existing wing panels in accordance with appendix 1 of Eiriavion Service Bulletin No. M 17, dated June 17, 1977, at an FAA certificated repair station that is a manufacturer's authorized repair facility. Following rebonding, visually inspect the affected area to ensure that the new resin forms a continuous bond on both sides of the wing shear web for its full length. (c) Repair in accordance with an alternate means of compliance which must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, Brussels, Belgium. NOTE: Copies of the applicable service bulletin are available at the following manufacturer's authorized repair facilities: Smitty's Soaring Service Deansboro Road Route 12B Clinton, New York 13323 Sailplane Repair Service, Inc. Rich Roberts 216 Commerce Drive P.O. Box 1462 Fort Collins, Colorado 80522 This amendment is effective August 8, 1977, as to all persons except those persons to whom it was made immediately effective by the telegram dated July 7, 1977, which contained this amendment.
2025-02-03: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by the discovery of ten ultrasonic inspections associated with airworthiness limitations (AWL) tasks and structural deviation inspection requirements (SDIR) tasks potentially not detecting cracks. This AD requires repetitive ultrasonic inspections of certain structural areas for cracking, and prohibits use of the previous revisions of certain procedures and mandates the use of the revised procedures when performing the inspections required by the associated AWL and SDIR tasks, as specified in a Transport Canada AD, which is incorporated by reference (IBR). This AD also requires repair of cracking. The FAA is issuing this AD to address the unsafe condition on these products.
2015-18-02: We are adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. This AD requires replacing the center wing box (CWB) and certain outer wings. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the CWB and outer wings are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking of the outer wings and the lower surface of the CWB, which could result in reduced structural integrity of the airplane.
86-11-01 R1: 86-11-01 R1 BOEING: Amendment 39-5322 as amended by Amendment 39-5550. Applies to all Model 747 airplanes, certificated in any category. To prevent wheel or tire failure as a result of failure of the wheel bearing, accomplish the following, unless already accomplished: \n\n\tA.\tWithin 100 flight cycles after the effective date of this AD, remove and inspect both the inner and outer wheel bearings, Timken P/N's LM229146 and LM229139, in accordance with the applicable portions of Sections 32-45-01 through 32-45-03 of the Boeing Model 747 maintenance manual. Any wheel bearing found damaged must be replaced with a new or serviceable bearing prior to further flight. \n\n\tNOTE: Serviceable bearings are those Timken bearings, P/N's LM229146 and LM229139, which have been inspected with a close visual inspection and found to have no visible damage (i.e., galling, gouging, spalling, overheat, etc.). \n\n\tB.\tAfter accomplishment of the inspection required by paragraph A., above, reinspectboth the inner and outer wheel bearings in accordance with the schedule below. Any wheel bearing found damaged as a result of the required inspections must be replaced with a new or serviceable bearing before further flight. \n\n\t\t1.\tBearings P/N LM229146 and LM229139, date stamped LS and subsequent, except those identified in subparagraph B.2., below, must be reinspected at intervals not to exceed 100 flight cycles. \n\n\t\t2.\tBearings date stamped LS and subsequent, which are installed on Boeing Model 747SR airplanes which have not incorporated Boeing Service Bulletin 747-32-2272 (which relates to gross weight increase), must be reinspected at intervals not to exceed 200 flight cycles. \n\n\tC.\tInstallation of inner and outer Timken wheel bearings, P/N's LM229147C and LM229140C, constitutes terminating action for the repetitive inspections required by paragraph B., above. \n\n\tD.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable levelof safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.\n \n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate an airplane to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tThe service information specified in this AD may be obtained upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. It may also 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\tAmendment 39-5322 became effective June 13, 1986. \n\tThis amendment, 39-5550, becomes effective February 26, 1987.
2002-05-06: This amendment supersedes an existing airworthiness directive (AD) for Sikorsky Aircraft Corporation Model S-76A helicopters that currently requires a service life limit on certain landing gear parts based on hours time-in-service (TIS). This amendment adds another method of calculating the life limit for certain landing gear parts based on cycles and requires the operator to choose and record the method of calculating the service life of each part in the rotorcraft history or equivalent record. This amendment also requires replacing the part based upon either the maximum hours TIS or the maximum cycles but not both. This amendment is prompted by the need to add flight cycles as a method of calculating the life limit for certain landing gear parts based on fatigue analyses. The actions specified by this AD are intended to add or revise the retirement life for certain landing gear parts to prevent fatigue failure of the landing gear and subsequent loss of control of the helicopter.
87-17-01: 87-17-01 SCHWEIZER AIRCRAFT CORP: Amendment 39-5973. Final copy of priority letter AD issued August 18, 1987. Applies to models (including kit built) SGU 1-7; SGS 2-8 (TG-2); SGS 2-12 (TG-3); SGU 1-19; SGU 1-20; SGU 1-21; SGU 2-22, 2-22A, 2-22C, 2- 22CK, 2-22E, 2-22EK; SGS 1-23, 1-23B, 1-23C, 1-23D, 1-23E, 1-23F, 1-23G, 1-23H, 1-23H15; SGS 1-24; SGS 1-26, 1-26A, 1-26B, 1-26C, 1-26D, 1-26E; SGS 2-32; SGS 2-33, 2-33A, 2- 33AK; SGS 1-34, 1-34R; SGS 1-35C; SGS 1-36 (SPRITE) gliders, certificated in any category. Compliance is required prior to the next flight after the effective date of this AD, unless already accomplished. To prevent the possibility of the tow release assembly creating a jammed condition during towing and subsequent failure of the tow line to release, which could result in a forced landing, accomplish the following: (a) Inspect the tow release installation to determine if any of the following release arms are installed: P/N 1D217-13, 1D222-15, 1D222-17 or 34017D-15. NOTE: The above arms can be identified by a lug which is welded on the front face of the release arm as shown in Figure 1 of Schweizer Service Bulletin (SB) No. SA-005.1, dated January 31, 1988. (b) Tow release installations which have any of the release arms listed in (a) must have the arms replaced in the following manner: P/N 1D217-13 replace with 1D217-09 P/N 1D222-15 replace with 1D222-11 P/N 1D222-17 replace with 1D222-13 P/N 34017D-15 replace with 34017D-11 (c) Perform the operational check in accordance with Figure 4 in Schweizer SB No. SA-001.3, dated January 31, 1988, following release arm replacement. (d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration (FAA), New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. Schweizer Aircraft Corporation SB No's. SA-005.1, and SA-001.3, both dated January 31, 1988, identified and described in this document, are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request from Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902; telephone (607) 739-3821. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Docket No. 87-ANE-29, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5973, becomes effective on August 19, 1988, as to all persons except those persons to whom it was made immediately effective by individual priority letter AD 87-17-01, issued August 18, 1987, which contained this amendment.