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87-25-03: 87-25-03 BRITISH AEROSPACE: Amendment 39-5779. Applies to British Aerospace Model 125-800A series airplanes, listed in British Aerospace (BAe) Service Bulletin 57-64-(3067), dated November 29, 1985, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent entrapment of water within the aileron tab accomplish the following: A. Within the next 100 landings or within one year after the effective date of this AD, whichever occurs sooner, modify the aileron tab and the inboard aileron hinge to provide drainage in accordance with BAe Service Bulletin 57-64-(3067), dated November 29, 1985. 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 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 13, 1988.
2006-17-08: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines that were reassembled with certain previously used high pressure compressor (HPC) exit brush seal assembly parts and certain new or refurbished HPC exit diffuser air seal inner lands. This AD requires replacing the HPC exit inner and outer brush seal packs with new brush seal packs, or replacing the HPC exit brush seal assembly with a new HPC exit brush seal assembly. This AD results from a report of oil leaking into the high pressure turbine (HPT) interstage cavity and igniting, leading to an engine case penetration and engine in- flight shutdown. Although liberated engine parts did not penetrate the engine nacelle, we are issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.
2018-14-10: We are superseding Airworthiness Directive (AD) 2017-12-03 for certain Pratt & Whitney Division (PW) PW2037, PW2037M, and PW2040 turbofan engines. AD 2017-12-03 required installing a software standard eligible for installation and precludes the use of electronic engine control (EEC) software standards earlier than SCN 5B/I. This AD requires installing a software standard eligible for installation and preclude the use of EEC software standards earlier than SCN 5B/I or SCN 27A. This AD was prompted by an unrecoverable engine in-flight shutdown (IFSD) after an ice crystal icing event. We are issuing this AD to address the unsafe condition on these products.
2000-08-21: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that requires repetitive inspections to detect cracking of the forward and aft inner chords and the splice fitting of the forward inner chord of the station 2598 bulkhead, and repair, if necessary. This amendment is prompted by reports of fatigue cracking found in those areas. The actions specified by this AD are intended to detect and correct such cracking, which could result in reduced structural capability of the bulkhead and the inability of the structure to carry horizontal stabilizer flight loads.
88-20-07: 88-20-07 BOEING: Amendment 39-6024. Applies to all Model 727 series airplanes, certificated in any category.\n \n\tCompliance required as indicated, unless previously accomplished. \n\n\tTo prevent jamming of the main landing gear door actuator caused by fracturing of the pivot trunnion, accomplish the following: \n\n\tA.\tWithin the next 1,600 flight cycles after the effective date of this AD, accomplish the visual inspection of the main landing gear door actuator pivots in accordance with Boeing Service Bulletin 727-32-0358, dated May 31, 1988. Repeat this inspection at intervals not to exceed 800 flight cycles. \n\n\tB.\tIf any of the pivot trunnion shafts are found loose or missing during the inspection performed in accordance with paragraph A., above, prior to further flight, replace the pivot in accordance with Boeing Service Bulletin 727-32-0358, dated May 31, 1988. \n\n\tC.\tAccomplishing the pivot replacement with a part number 3-3141-54 pivot, in accordance with Sargent Controls Service Bulletin 7-3141-32-06, Revision 1, dated November 2, 1987, constitutes terminating action for the initial and repetitive inspections required by paragraph A., above. \n\n\tD.\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\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington, 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or Seattle Aircraft CertificationOffice, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis Amendment, 39-6024, becomes effective November 1, 1988.
2006-17-11: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-400ER series airplanes and Model 777-200 and - 300 series airplanes. This AD requires, for certain airplanes, repetitive testing of the fill and safety fittings of the cargo fire extinguishing bottles in the forward cargo compartment for leaks; and repetitive application of a corrosion inhibiting compound (CIC) or replacement of the cargo fire extinguishing bottles with reworked fire extinguishing bottles, as necessary. For all airplanes, this AD requires replacement of the cargo fire extinguishing bottles with reworked fire extinguishing bottles, which ends the repetitive tests and CIC applications if applicable. This AD results from failure of the safety fittings for the cargo fire extinguishing bottles. We are issuing this AD to prevent failure of the safety fittings for the cargo fire extinguishing bottles due to corrosion, which could result in leakage of extinguishing agent. If a fire occurs in the cargo bay, the cargo fire extinguishing bottles could have less than enough extinguishing agent to control a fire.
2000-08-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon Model BAe 125-800A and BAe 125-800B, Model Hawker 800, and Model Hawker 800XP series airplanes, that currently requires the filling of two tooling holes on the firewalls of the left and right engine pylons with firewall sealant. This amendment requires the sealing of all unused (open) tooling holes on the firewalls of the left and right engine pylons, and expands the applicability to include additional airplanes. This amendment is prompted by reports of additional unused (open) tooling holes, found at locations other than those currently addressed. The actions specified by this AD are intended to prevent an engine fire from moving to the fuselage and to the lines that carry flammable fluid that are located inboard of the firewall. The incorporation by reference of Raytheon Service Bulletin SB.54-1-3815B, dated March 26, 1996, as listed in the regulations, was approved previously by the Director of the Federal Register as of January 27, 1997 (61 FR 66878, December 19, 1996).
2018-17-09: We are superseding Airworthiness Directive (AD) 2014-05-28, which applied to certain Bombardier, Inc., Model DHC-8-400 series airplanes. AD 2014-05-28 required revising the maintenance or inspection program, as applicable. This AD requires revising the maintenance or inspection program, as applicable, to include a revised task. This AD was prompted by a determination that the interval from Maintenance Review Board (MRB) task number 323100-202 should not be escalated, and that Certification Maintenance Requirements (CMR) task number 323100-102 should be applicable to all Model DHC-8-400 series airplanes, regardless of which main landing gear (MLG) up-lock assembly is installed. We are issuing this AD to address the unsafe condition on these products.
86-24-04: 86-24-04 BRITISH AIRCRAFT CORPORATION: Amendment 39-5477. Applies to Model 1-11 200 and 400 series airplanes, modified in accordance with Air Cruisers Company STC SA840EA, as listed in Air Cruisers Company Alert Service Bulletin 203-25-A2, dated November 17, 1986, certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude the potential for jamming of the passenger or service doors, accomplish the following: A. Within the next 10 hours time-in-service and at intervals not to exceed 120 hours time-in-service thereafter, perform the visual inspection of the container latch release cable, and replace, if necessary, in accordance with Air Cruisers Alert Service Bulletin 203-25-A2, dated November 17, 1986, or later FAA-approved revisions. B. Prior to modification of any airplane in accordance with Air Cruisers Company STC SA840EA, visually inspect the container latch release cable and replace, if necessary, in accordancewith Paragraph 3.0 of Air Cruisers Alert Service Bulletin 203-25-A2, dated November 17, 1986, or later FAA-approved revisions. C. Inspections required by paragraph A., above, may be discontinued upon incorporation of a modification approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD may be accomplished. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Air Cruisers Company, P.O. Box 180, Belmar, New Jersey 07719-0180. 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 becomes effective December 19, 1986.
67-17-02: 67-17-02 BRITISH AIRCRAFT: Amdt. 39-421 Part 39 Federal Register May 18, 1967. Applies to Model BAC 1-11 Series Airplanes. Compliance required within the next 1,000 hours' time in service after the effective date of this AD, unless already accomplished. To prevent a potential fire hazard in the forward and aft freight compartments, modify the light assemblies, as shown in the table (below), by providing ventilating holes in the light cup assemblies and by replacing the nylon lamp cover with a 5/32 inch toughened glass lamp cover, or FAA-approved equivalent, in accordance with British Aircraft Corporation BAC 1-11 Service Bulletin No. 33-PM 1706, or later ARB-approved issue. Sta. No. Mod.App. Pre-Mod.BAC P/N Post Mod.BAC P/N 200 Ser.Post Mod.P/N 400 256 200&400 AB 28A 15593 AC 28A 5099 AK 28A 26277 296 200&400 AB 28A 15591 AC 28A 5097 AC 28A 5097 336 200&400 AB 28A 15593 AC 28A 5099 AK 28A 26277 376 200&400 AB 28A 15591 AC 28A 5097 AC 28A 5097 396 200&400 AB 28A 15593 AC 28A 5099 AC 28A 5099 670 200&400 AB 27A 17335 AC 27A 5487 AC 27A 5487 710 200&400 AB 28A 15591 AC 28A 5097 AC 28A 5097 750 200 Ser. AB 27A 17336 AC 27A 14439 750 400 Ser. AB 27A 17335 AC 28A 14439 This directive effective June 17, 1967.