Results
73-14-07: 73-14-07 GRUMMAN AMERICAN AVIATION CORPORATION (GAAC): Amendment 39-1684 as amended by Amendment 39-1970. Applies to all G-159 airplanes, and to G-1159 airplanes, Serial Numbers 1 through 129 and 775, certificated in all categories. Compliance required as indicated. To detect fuselage aft section pressure dome cracks and prevent further cracking, accomplish the following: (a) Within 200 hours time in service after the effective date of this AD or 90 days, whichever is the sooner, unless already accomplished, permanently remove all interior lining attachments other than fabric, carpeting, etc., from the fuselage aft section pressure dome assembly, Part No. 1159B21372 (G-1159), Part No. 159B10252 (G-159) and inspect for cracks in accordance with GAAC Customer Bulletins 167 (G-1159) or 240 (G-159), dated June 18, 1973 or later FAA approved revisions placing emphasis on those areas as defined in paragraph (b). (b) Mark the exact location on the dome and record the geometric configuration of items removed in accordance with paragraph (a), noting the location of any discontinuities, particularly in radially running attachment strips. The FAA would appreciate receiving sketches and descriptive data of both the attachment location and geometric configurations. Sketches and descriptive data may be sent to the Chief, Engineering and Manufacturing Branch, Southern Region, P. O. Box 20636, Atlanta, Georgia 30320. (c) For aircraft found to have no attachments on the dome, no further action is required. (d) For aircraft having attachments, reinspect for cracks at intervals not to exceed 400 landings (G-1159) or 4000 landings (G-159), since the last inspection, in accordance with GAAC Customer Bulletins 167 (G-1159) or 240 (G-159). (e) Repair all cracks detected during the inspections conducted in accordance with (a) or (d). Repair in accordance with GAAC Customer Bulletins 167 (G-1159) or 240 (G-159), before further flight. (f) For the purpose of complying with paragraph (d) of this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hour's time in service by the operator's fleet average time from takeoff to landing for the airplane type. (g) Airplanes having cracked domes may be flown to a base for repairs in accordance with FAR 21.197 either: (1) Unpressurized, or (2) With limited pressurization with the concurrence of the FAA, Chief, Engineering and Manufacturing Branch, Southern Region. Amendment 39-1684 became effective July 16, 1973. This Amendment 39-1970 becomes effective September 30, 1974.
99-23-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Eurocopter France Model SA330F, G, J, and AS332C, L, and L1 helicopters. This action requires inserting statements into the Limitations section of the Rotorcraft Flight Manual (RFM) prohibiting flight under certain atmospheric conditions. This amendment is prompted by one incident in which a Multi-Purpose Air Intake (MPAI) inlet seal deflated after the P2 air system line, which feeds the seal, clogged due to the formation of ice. The actions specified in this AD are intended to prevent clogging of the MPAI seal P2 air system line due to ice formation, which could result in deflation of the MPAI seal, loss of engine power, and subsequent loss of control of the helicopter.
2014-06-03: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as stress corrosion cracking of the main landing gear yoke pintle housing on a Jetstream series 3100 airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
99-22-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and 340B series airplanes, that requires removal of certain main landing gear downlock and brake hydraulic swivel brackets and replacement with new, redesigned brackets. 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 downlock or brake swivels. Brake swivel failure could cause the loss of inboard or outboard brakes. Downlock swivel failure could cause the loss of hydraulic fluid in the main hydraulic system, as well as the loss of nose wheel steering operation, extension and retraction capability of landing gear and flaps, and operation of the propeller brake (if installed).
91-19-01: 91-19-01 CANADAIR, LTD.: Amendment 39-8026. Docket No. 91-NM-161-AD. Applicability: Model CL-600-1A11 series airplanes, serial numbers 1004 through 1085; Model CL-600-2A12 series airplanes, serial numbers 3001 through 3066; and Model CL-600-2B16 series airplanes, serial numbers 5001 through 5098; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of emergency power to the essential bus when the air driven generator (ADG) is deployed, accomplish the following: (a) Within 25 hours time-in-service after the effective date of this AD, inspect the ADG wiring harness to detect chafing, in accordance with Canadair Service Bulletin A600-0612 (for Model CL-600-1A11 series airplanes), dated April 24, 1991, or Canadair Service Bulletin A601-0370 (for Model CL-600-2A12 and CL-600-2B16 series airplanes), dated April 24, 1991. If chafing is found, prior to further flight, repair in accordance with the applicable service bulletin previously described. (b) Within 60 days after the effective date of this AD, modify the ADG harness installation in accordance with Canadair Service Bulletin A600-0612 (for Model CL-600-1A11 series airplanes), dated April 24, 1991, or Canadair Service Bulletin A601-0370 (for Model CL- 600-2A12 and CL-600-2B16 series airplanes), dated April 24, 1991. (c) An alternative method 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, ANE-170, FAA, Engine and Propeller Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New York Aircraft Certification Office, ANE-170. (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 thisAD. (e) The inspection, repair, and modification requirements shall be done in accordance with Canadair Service Bulletin A600-0612 (for Model CL-600-1A11 series airplanes), dated April 24, 1991, or Canadair Service Bulletin A601-0370 (for Model CL-600-2A12 and CL-600-2B16 series airplanes), dated April 24, 1991. 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 Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station A, Montreal, Quebec, Canada H3C 3G9. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8026, AD 91-19-01) becomes effective on September 24, 1991.
2014-05-10: We are superseding Airworthiness Directive (AD) 2012-25-04 for Eurocopter France Model AS350B3 helicopters with a certain modification (MOD) installed. AD 2012-25-04 required installing two placards and revising the Rotorcraft Flight Manual (RFM). AD 2012-25-04 also required certain checks and inspecting and replacing, if necessary, all four laminated half-bearings (bearings). This new AD retains the previous AD requirements, requires certain modifications which would be terminating action for the airspeed limitations, and adds certain helicopter models to the bearing inspection with a different inspection interval. These actions are intended to prevent vibration due to a failed bearing, failure of the tail rotor, and subsequent loss of control of the helicopter.
2006-04-07: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes, that requires installation of a linear fluid- filled damper between each elevator surface and the airplane structure on both the left and right sides of the airplane, along with related structural and system modifications. The actions specified by this AD are intended to prevent pitch oscillation (vertical bouncing) of the fuselage due to excessive ice buildup on the elevator servo tab, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
96-13-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) Jetstream Model 3201 airplanes. This action requires repetitively inspecting the spigot housing plate for cracks and corrosion at the wing/fuselage forward attachment sliding joint, replacing any cracked or corroded part, and eventually replacing the spigots and spigot housing plate with new parts of improved design. A crack in the spigot housing plate assembly found during fatigue testing of the affected airplanes prompted this action. The actions specified by this AD are intended to prevent structural failure of the wing/fuselage area caused by a cracked or corroded spigot housing assembly.
46-14-01: 46-14-01 FAIRCHILD: (Was Mandatory Note 5 of AD-724-2.) Applies to Model M- 62C Aircraft. Inspect indexing of fixed pitch wood propeller on engine crankshaft. To reduce possibility of crankshaft failure, fixed pitch wood propeller must be installed in the 90 degree position (blades at right angles to the crankthrow.)
98-02-06 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing 777-200 series airplanes, that currently requires repetitive visual inspections to determine the presence and condition of the nut and cotter pin of the lock link mechanism on the side struts and drag struts on the main landing gear (MLG); and corrective action, if necessary. That AD was prompted by reports of missing or damaged components on the lock link mechanism. The actions specified by that AD are intended to prevent failure of the lock link mechanism to lock the MLG in the down position, and consequent collapse of the MLG during ground operation. This amendment provides an optional terminating action for the repetitive inspections.
99-21-30: This amendment adopts a new airworthiness directive (AD), applicable to all Raytheon Model Mitsubishi MU-300 airplanes, that requires revising the Airplane Flight Manual (AFM) to provide pilots with certain operating procedures during icing conditions, and to limit the maximum flaps position for flight in icing conditions or landing after an icing encounter. The amendment also requires installing an ice detector, and accomplishing a corresponding AFM revision to address its operation. For certain airplanes, the amendment requires converting the airplane configuration or modifying the warning horn system of the landing gear; and revising the AFM to specify flaps 10 degrees as a normal landing flap configuration. The actions specified by this AD are intended to prevent uncommanded nose-down pitch at certain flap settings during icing conditions.
87-03-05: 87-03-05 BRITISH AEROSPACE: Amendment 39-5516. Applies to Model BAe 125- 800A and -800B series airplanes, listed in British Aerospace Service Bulletin 53-59 (3031B), dated June 5, 1986, certificated in any category. Compliance is required prior to the accumulation of a total of 3,000 flight cycles, or within the next 90 days after the effective date of this AD, whichever occurs later. To prevent the possible rapid loss of cabin pressurization, accomplish the following, unless previously accomplished: A. Modify the fuselage canopy upper rail in accordance with Section 2, "Accomplishment Instructions," of British Aerospace Service Bulletin 53-59-(3031B), dated June 5, 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 service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian for Service Bulletins, Box 17414, Dulles International Airport, Washington, D.C. 20041. 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 February 19, 1987.
2014-04-09: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD will complete certain mandated programs intended to support the airplane reaching its limit of validity \n\n((Page 17406)) \n\n(LOV) of the engineering data that support the established structural maintenance program. This AD requires repetitive inspections for cracking of small repairs done on the vertical flange of the rib chord, repetitive inspections for cracking along the upper fillet radius of the rib chord, and a large repair or preventive modification if necessary. Accomplishment of a large repair or preventive modification terminates the actions of this AD. We are issuing this AD to prevent cracks in the rib upper chord, which could result in the inability of the wing structure to support the limit load condition, and consequent loss of structural integrity of the wing.
86-04-06: 86-04-06 FOKKER B.V.: Amendment 39-5230. Applies to Model F27 airplanes, serial numbers 10105 to 10635 inclusive, certificated in any category. Compliance is required within 180 days after the effective date of this AD, unless already accomplished: A. To prevent restricted aileron movement or jamming, modify the aileron inboard hinge bolt installations in accordance with Fokker Service Bulletin F27/57-58, dated May 16, 1983. B. Alternate means of compliance which provide 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 these documents from the manufacturer may obtain copies upon request to the Manager, Maintenance and Engineering, Fokker B.V., Product Support, P.O. Box 7600, 11172J Schiphol Oost, The Netherlands. These documents 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 14, 1986.
99-22-12: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS332C, L, and L1 helicopters, that requires replacing certain electrical modules with airworthy electrical modules. This amendment is prompted by the discovery of several defective electrical modules. The actions specified by this AD are intended to prevent loss of electrical continuity, which could cause loss of critical systems and subsequent loss of control of the helicopter.
2022-18-18: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of a failed extension of inboard slats during the landing phase, which was not indicated to the flightcrew by the crew alerting system. This AD requires revising the existing airplane flight manual (AFM) to provide procedures for failed extension of inboard slats and flightcrew indication during landing, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2014-05-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727 airplanes. This AD was prompted by certain mandated programs intended to support the airplane reaching its limit of validity of the engineering data that support the established structural maintenance program. This AD requires an inspection for cracks in the main wheel well pressure floor and a preventive modification or permanent repair, as applicable. We are issuing this AD to prevent cracking in the main wheel well pressure floor, which could result in reduced structural integrity of the airplane, and decompression of the cabin.
99-22-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 series airplanes, that requires modification of the wiring of the emergency lighting system. 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 the pilots from having full authority over the cabin emergency lights, which could result in delayed egress of the passengers and crew from the cabin during emergency evacuation.
99-22-05: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 series airplanes, that requires repetitive inspections of the elevator trim control cables for signs of wear damage or broken wires; replacement of damaged or broken cables with certain new cables; and replacement of all 7x7 cables with 7x19 cables. 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 elevator trim cable due to fatigue cracking, which if not corrected, could result in reduced controllability of the airplane.
81-07-51 R1: 81-07-51 R1 SIKORSKY AIRCRAFT: Amendment 39-4130 as amended by Amendment 39-4211. Applies to S-76A series helicopters certificated in all categories. Compliance required as indicated. To prevent fracture of main rotor spindles, accomplish the following: 1. For main rotor spindles, P/N 76102-08001-041 series, with more than 200 hours time in service on March 20, 1981, compliance required prior to further flight, unless already accomplished within the last 100 hours time in service, and thereafter for all spindles upon removal and/or replacement of either the main rotor spindle, P/N 76102-08001-041 series, the spindle bearing inner race, P/Ns SB 5206-102/-103/-104, or the spindle bearing outer race, P/N SB 5206-202. Remove and fluorescent penetrant inspect main rotor spindles, P/N 76102-08001-041 series, for cracks in accordance with Sikrosky Alert Service Bulletin 76-65-13A, paragraph G(6), dated April 24, 1980, or later FAA approved revision. If a crackindication is found, replace the main rotor blade spindle with a new or serviceable main rotor blade spindle, prior to next flight, in accordance with Sikorsky S-76A Maintenance Manual, SA4047-76-2, Section 65-12-02. 2. Prior to further flight, remove from service all main rotor spindles, P/N 76102-08001-041 series, with 700 or more hours time in service, and replace with a serviceable spindle in accordance with the instructions contained in Chapter 65 of the Sikorsky S-76A Maintenance Manual, SA4047-76-2. 3. Thereafter, remove from service all spindles, P/N 76102-08001-041 series, upon accumulation of 700 hours time in service, and replace with a serviceable spindle in accordance with the instructions contained in Chapter 65 of the Sikorsky S-76A Maintenance Manual, SA4047-76-2. 4. For main rotor spindles, P/N 76102-08001-041 series, or spindle shear bearing inner races, P/N SB 5206-202, with more than 200 hours time in service on March 20, 1981, compliance required within the next 5 hours time in service after March 20, 1981, unless already accomplished, and thereafter for all spindles upon removal and/or replacement of either the main rotor spindle, P/N 76102-08001-041 series, the spindle bearing inner race, P/Ns SB 5206-102/-103/-104, or the spindle bearing outer race, P/N SB 5206-202. Inspect the shear bearing inner/outer races fob diametrical clearance, and replace the main rotor spindle if the diametrical clearance exceeds 0.015 inches, in accordance with Sikorsky Customer Service Bulletin No. 76-65-22B, paragraph G(2), dated May 1, 1981, or later FAA-approved revision. Spindles known to have operated with less than 10 hours time in service with diametrical clearances in excess of 0.015 inches may be returned to service. 5. For all main rotor spindles with more than 200 hours time in service on March 20, 1981, and on all other spindles before the accumulation of 225 hours time in service which do not have a record of Kahr bearings installed, compliance required within the next 25 hours time in service after March 20, 1981, unless already accomplished, and thereafter for all spindle/bearings at intervals not to exceed 350 hours time in service. Inspect for wear and vendor origin the main rotor spindle shear bearings outer race, P/N SB 5206-202, and inner race, P/Ns SB 5206-102/-103/-104, and replace, as necessary, in accordance with Sikorsky Customer Service Bulletin No. 76-65-22B, paragraphs G(4) and G(5), dated May 1, 1981, or later FAA-approved revision. 6. Aircraft may be ferried to a base for compliance with this AD in accordance with Section 21.197 of the Federal Aviation Regulations. 7. Upon request of the operator, an alternate means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 8. Report within 24 hours any discrepancies found and the spindle time in service to the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Reporting approved by the Office of Management and Budget under OMB No. 04-R0174. 9. Prior to December 15, 1981, remove from service all spindle/cuff assemblies, P/N 76102-08001-041, and replace with spindle/cuff assemblies, P/N 76102-08001-043, with spindle preload bolt P/N 76102-08051-103/-104 in accordance with Sikorsky Service Bulletin No. 76-65-24B, dated 8-17-81, or later FAA approved revision. Mandatory requirements for the inspection and replacement of the spindle/cuff assemblies and the shear bearings continue in effect for the P/N 76102-08001-043 assemblies and have been incorporated in Chapter 4 of the Sikorsky S-76A Maintenance Manual, SA 4047-76-2, Airworthiness Limitations Section. 10. Installation of P/N 76102-08001-043 spindle/cuff assemblies with the 76102-08051-103 or -104 spindle preload bolts terminates the requirements ofAD 81-07-51. 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). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Sikorsky Aircraft, Division of United Technologies Corporation, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. Amendment 39-4130 became effective June 11, 1981, as to all persons except those persons to whom it was made immediately effective by the telegram dated March 20, 1981. This amendment 39-4211 becomes effective September 21, 1981.
2014-05-19: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-200B, 747-200F, 747-300, 747SP, 747-400, and 747-400F series airplanes equipped with Rolls-Royce RB211-524 engines; and certain Model 767-300 series airplanes equipped with Rolls-Royce RB211-524 engines. This AD was prompted by multiple reports of uncommanded thrust reverser unlock events. This AD requires replacing certain relays and relay sockets, and doing wiring changes. For certain airplanes, this AD also requires installing new relay panels, and removing and installing certain components. Additionally, this AD requires, for certain airplanes, accomplishing concurrent actions, which include installing an additional locking system on the thrust reversers and modifying system wiring for in-flight fault indications of the thrust reverser system. We are issuing this AD to prevent an uncommanded thrust reverser deployment during takeoff or in flight, resulting in decreased airplane control and performance, possible runway excursions, and failure to climb.
2010-16-06: We are adopting a new airworthiness directive (AD) for certain Model 737-300, -400, -500, -600, -700, and -800 series airplanes. This AD requires inspecting to verify the part number of the low-pressure flex-hoses of the crew oxygen system installed under the oxygen mask stowage boxes located within the flight deck, and replacing the flex- hose with a new non-conductive low-pressure flex-hose if necessary. This AD results from reports of low-pressure flex-hoses of the crew oxygen system that burned through due to inadvertent electrical current from a short circuit in the audio select panel. We are issuing this AD to prevent inadvertent electrical current, which can cause the low- pressure flex-hoses of the crew oxygen system to melt or burn, causing oxygen system leakage and smoke or fire.
99-22-02: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 757-200PF series airplanes, that requires revising the Airplane Weight & Balance (W&B) Manual to prohibit operation of any airplane without side vertical restraints installed on the main cargo deck when carrying a particular pallet. This amendment also provides for optional terminating action for the Airplane W&B Manual revision. This amendment is prompted by reports indicating that some airplanes have been operated without side vertical restraints installed on the main cargo deck when carrying certain pallets. The actions specified by this AD are intended to prevent inadvertent movement of a cargo pallet during flight, which could result in an adverse center of gravity condition and consequent reduced controllability of the airplane.
90-07-01: 90-07-01 BRITISH AEROSPACE: Amendment 39-6550. Docket No. 89-NM-229-AD. Applicability: Model BAe 146-100A series airplanes, Serial Numbers E1002 through E1100, E1102, and E1103; Model BAe 146-200A series airplanes, Serial Numbers E2012 through E2113, E2115 and E2118; and Model BAe 146-300A series airplanes, Serial Numbers E3118 through E3123 and E3125; certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent loss of asymmetry protection and loss of airplane controllability, accomplish the following: A. Install a warning placard on shelf No. 5 beneath the flap computer, in accordance with British Aerospace Service Bulletin 11-36-01104A&B, dated May 10, 1989, stating: WARNING - THIS EQUIPMENT MUST NOT BE REMOVED OR RE-RACKED IN FLIGHT B. Install a warning placard on circuit breaker panel 131-11-00, in accordance with British Aerospace Service Bulletin 11-36-01104A&B, dated May 10, 1989, stating: WARNING C/BREAKERS MUST NOT BE PULLED IN FLIGHT. 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. 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. 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 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, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6550, AD 90-07-01) becomes effective on April 30, 1990.
2022-14-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a report from Boeing that Rolls-Royce Deutschland Ltd & Co KG (RRD) discovered a design issue in the engine fuel feed system, which could result in fuel flow restrictions to both engines when ice that has accumulated in the airplane fuel feed system suddenly releases into the engines. This AD requires revising the existing airplane flight manual (AFM) to update the limitations on minimum fuel temperatures. The FAA is issuing this AD to address the unsafe condition on these products.