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86-21-01: 86-21-01 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5431. Applies to all Aerospatiale Model SA 365 series helicopters certificated in all categories. Compliance is required as indicted, unless already accomplished. To prevent failure of the main rotor head sleeves, accomplish the following: (a) For those helicopters exhibiting a severe tracking defect, inspect the main rotor head sleeves as follows before further flight: (1) Remove main rotor blades and visually inspect the sleeves for cracks, delaminations, or separated bushes; and (2) Replace any sleeves found damaged with serviceable sleeves. (b) For Model SA 365C, C1, C2, and C3 helicopters, replace Part Numbers (P/N's) 365A.31.1831.00, .01, .02, .03, and 365A31.1851.00 and .01 main rotor head sleeves as follows: (1) For sleeves which have 1,900 or more hours' time in service on the effective date of this AD, replace the sleeves within 100 hours' time in service; and(2) For sleeves which have less than 1,900 hours' time in service on the effective date of this AD, replace the sleeves before they reach 2,000 hours' time in service. (c) For Model SA 365N and N-1 helicopters, replace P/N's 365A31.1829.02 and .03 and 365A31.1828.00 and .01 main rotor head sleeves as follows: (1) For sleeves which have 900 or more hours' time in service on the effective date of this AD, replace the sleeves within 100 hours' time in service; and (2) For sleeves which have less than 900 hours' time in service on the effective date of this AD, replace the sleeves before they reach 1,000 hours' time in service. (d) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101, or by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (e) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the maintenance required by this AD may be accomplished. NOTE: Aerospatiale Telex Service SA 365C Nos. 01.18 and .01.19 and Aerospatiale Telex Service SA 365N-FS No. 01.18 pertain to this subject. This amendment becomes effective October 24, 1986.
87-25-06: 87-25-06 BRITISH AEROSPACE: Amendment 39-5788. Applies to all Model H.S. 748 series airplanes as listed in BAe Service Bulletin 78/9, Revision 1, dated September 1985, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent inflight loss of the jet pipe or restricted fuel drainage through the jet pipe retention assemblies, with resultant fire or heat damage to the nacelle and wing, accomplish the following: A. Within the next 60 days after the effective date of this AD, perform an inspection to ensure correct installation of the three retaining plate assemblies, which secure the jet pipe inside the jet pipe manifold, in accordance with British Aerospace Service Bulletin 78/9, Revision 1, dated September 1985. Any discrepancies found must be corrected prior to further flight. B. Repeat the inspection required by paragraph A. above, any time the jet pipe is replaced. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. 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 proposal who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, 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, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment becomes effective January 19, 1988.
2010-23-15: We are adopting a new airworthiness directive (AD) for certain Model 777-200, -200LR, -300, and -300ER series airplanes. This AD requires removing and repairing the sealant at the four lower corners of the wing center section and the four lower t-chord segment gaps on each side of the wing center section. This AD results from reports of fuel leakage from the center tank. We are issuing this AD to detect and correct improperly applied sealant, which could result in the disbonding and displacing of sealant, and consequent fuel leaks. On the ground, uncontained fuel leakage could result in pooling, and pooling combined with an ignition source could result in a fire.
96-18-05 R1: This amendment revises an existing airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 206L, 206L-1, and 206L-3 helicopters with a certain part numbered tailboom installed, that currently requires a visual inspection of the tailboom skin in the areas around the nutplates and in the areas of the tailboom drive shaft cover retention clips for cracks and corrosion using a 10-power or higher magnifying glass until the tailboom is replaced with an airworthy tailboom. This action requires the same actions as the existing AD, but allows a longer interval for the repetitive inspections if the tailboom is modified to increase its structural integrity. Replacement with an airworthy tailboom other than a part- numbered tailboom affected by this amendment constitutes a terminating action for the requirements of this AD. This amendment is prompted by an accident and several reports of fatigue cracks in the tailboom skin in the areas around the nutplates for the tail rotor fairing and in the areas of the tail rotor drive shaft cover retention clips. The actions required by this AD are intended to prevent failure of the tailboom and subsequent loss of control of the helicopter.
87-04-18: 87-04-18 SHORT BROTHERS PLC: Amendment 39-5551. Applies to Model SD3-30 airplanes, Serial Numbers SH3002 through SH3116 inclusive, certificated in any category. Compliance is required within 90 days after the effective date of this AD, unless previously accomplished: A. To prevent fuel entering into the main cabin, seal certain areas of the fuselage top skin in accordance with Short Brothers PLC, Service Bulletin SD330-53-58, dated January 1986, or Revision 1, dated May 1986. 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. 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 the modification required by this AD. All persons affected by this directive who have not already received the appropriate servicedocument from the manufacturer may obtain copies upon request to Short Brothers PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. 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. This amendment becomes effective March 18, 1987.
2010-23-13: We are adopting a new airworthiness directive (AD) for all Model 757 airplanes. This AD requires changing the lower fixed leading edge panel assemblies immediately outboard of the nacelles at slats 4 and 7. This AD results from reports of Model 757 airplanes in service that have drain holes and unsealed panel assemblies in the fixed leading edge adjacent to the inboard end of slats 4 and 7 that are too close to the hot portion of the engines. We are issuing this AD to prevent fuel leaking onto an engine and a consequent fire.
89-04-07: 89-04-07 CANADAIR: Amendment 39-6141. Applicability: Model CL-44D4 and CL-44J series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent wing failure due to exfoliation corrosion on the wing upper skin, accomplish the following: A. Within 225 hours time-in-service or 30 days after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 12 months, perform a visual inspection of the upper wing skin area between the front and rear spars over the total wing span for corrosion, including raised blistering or bulging, in accordance with Canadair Alert Wire 44T-1340/2431, dated October 28, 1988. 1. If the extent of such corrosion exceeds 20 sq.in. in any one skin panel, between chordwise joints, prior to further flight conduct a non-destructive testing (NDT) inspection, using ultrasonic or eddy current inspection techniques, to determine the skin thickness,in accordance with the Alert Wire. Repair the corrosion area prior to further flight, in accordance with a method approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. 2. If the extent of such corrosion exists within an area equal to or less than 20 sq.in. in any one skin panel, between chordwise joints, repair corrosion area within 900 hours time-in-service or 6 months after the effective date of this AD, whichever occurs first. Repair must be accomplished in accordance with a method approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. B. Within 48 hours after performing the inspections required by paragraph A., above, submit a report of results to Canadair, in accordance with Canadair Alert Wire 44T- 1340/2431, dated October 28, 1988. The report must include information as to the extent and location of the corrosion, and the inspection method used. 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, New York Aircraft Certification Office, FAA, New England 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, New York 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 information from the manufacturer may obtain copies upon request to Bombardier, Inc., Canadair Aerospace Group, P.O. Box 6087, Station A, Montreal, Quebec H3C 3G9, Canada. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6141, AD 89-04-07) becomes effective March 7, 1989.
87-18-07: 87-18-07 ROLLS-ROYCE plc (formerly Rolls-Royce Limited): Amendment 39-5689. Applies to Rolls- Royce (R-R) Spey 506-14, 506-14A, 506-14D, 511-5W, 511-14, 511-14W, 511-8, 511-8/Mod. 2970, 512-14E, 512-14DW, 512-5, 512-5W, 555-15, 555-15H, 555-15N, and 555-15P turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent failure of the primary airscoop and subsequent burnthrough of the engine case, inspect for cracks, and repair or replace as necessary, the primary airscoops in accordance with R-R Service Bulletin (SB) Number SP72-997, dated October 1985, at the next engine shop visit after the effective date of this AD. NOTE: For the purpose of this AD, engine shop visit is defined as the input of an engine to a repair shop where combustion section system overhaul facilities exist and the subsequent engine maintenance entails the separation of front and rear. Aircraft may be ferried in accordance with the provisions of FAR 21.197and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. R-R SB Number SP72-997, dated October 1985, identified and described in part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Service Manager, Spey Engine, Rolls-Royce plc, East Kilbride, Glasgow G74 4PY, Scotland. This document 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, Rules Docket Number 86-ANE-24, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment becomes effective on September 28, 1987.
89-12-09: 89-12-09 AEROSPATIALE: Amendment 39-6231. Applicability: All Model ATR42 series airplanes, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent a fire in a cargo compartment remaining undetected, accomplish the following: A. Modify the forward and aft smoke detector test systems, in accordance with Aerospatiale Service Bulletin ATR42-26-0010, Revision 1, dated March 28, 1989. 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 will either concur or comment 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 in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Aerospatiale, 216 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6231, AD 89-12-09) becomes effective on June 20, 1989.
88-17-02 R2: 88-17-02 R2 FOKKER: Amendment 39-6035 as revised by Amendment 39-6127 is further revised by Amendment 39-6331. Docket No. 89-NM-82-AD. Applicability: Model F-27 series airplanes, serial numbers 10346 to 10684, inclusive; and serial numbers 10105 to 10345, inclusive, if retrofitted with outerwing serial number 246 or higher; certificated in any category. Compliance: Required as indicated unless previously accomplished. To prevent reduced structural capability of the wing, accomplish the following: A. Within 24 hours after February 15, 1989 (the effective date of Amendment 39- 6127), incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD into the AFM. "For airplanes operating at weights over 32,000 lbs.: Speed Limitation VB: 165 KIAS (168 KTS CAS)" B. Within 24 hours after February 15, 1989 (the effective date of Amendment 39- 6127), install a placard near each airspeed indicator, stating the following: FOR AIRPLANES OPERATING AT WEIGHTS OVER 32,000 LBS.: SPEED LIMITATION VB: 165 KIAS (168 KTS CAS) C. Within six months after the effective date of this amendment, perform a one-time inspection of the splice parts at Wing Station 7915, in accordance with the Accomplishment Instructions, Part 1, Fokker Service Bulletin F27/57-63, Revision 1, dated January 25, 1989. 1. If no defective splice parts are found, and if the structural strength of the wing splice is determined to be satisfactory in accordance with the limits specified in the service bulletin, no further action is required. The airspeed restriction required by paragraphs A. and B., above, is no longer required, and the AFM limitation and placard may be removed. 2. If defective splice parts are found or if the structural strength of the wing splice is determined to be unsatisfactory in accordance with the limits specified in the service bulletin, within one year after the effective date of this amendment reinforce all unsatisfactory splice parts at Wing Station 7915 in accordance with the Accomplishment Instructions, Part 2, of Fokker Service Bulletin F27/57-63, Revision 1, dated January 25, 1989. Following this modification and a determination that the wing splice strength is satisfactory, the airspeed restriction required by paragraphs A. and B., above, is no longer required, and the AFM limitation and placard may be removed. 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, Northwest Mountain 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 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 Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. Priority Letter AD 88-17-02, issued on August 15, 1988, became effective immediately upon receipt. Amendment 39-6035, the Final Rule of AD 88-17-02, became effective on October 14, 1988, and was revised by Amendment 39-6127, AD 88-17-02 R1, which became effective on February 15, 1989. This Amendment (39-6331, AD 88-17-02 R2) revises AD 88-17-01 R1 and becomes effective onOctober 30, 1989.