Results
82-17-01: 82-17-01 HUGHES HELICOPTERS, INC.: Amendment 39-4433. Applies to Model 369D helicopters certificated in all categories, equipped with main transmission part number 369D25100 - basic configuration. Compliance is required as indicated, unless already accomplished. To prevent failure of the output gearshaft assembly, P/N 369D25132, accomplish the following: (A) Within 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 300 hours' time in service, until such time as the ultrasonic inspection of paragraph (B) of this AD is accomplished, conduct a visual inspection for cracks in the transmission output shaft in accordance with instructions in Part I entitled "Periodic Visual Inspection" of Hughes Service Information Notice No. DN-105 dated May 25, 1982, (hereinafter referred to as DN-105), or FAA approved equivalent. (B) The visual inspections required by paragraph (A) of this AD may be discontinued by conducting a one-time ultrasonic inspection of the electron beam weld area of the transmission output shaft in accordance with the instructions of Part II entitled "Ultrasonic Inspection" of DN- 105, or FAA approved equivalent. This inspection must be accomplished no later than the next overhaul or major disassembly of the transmission. (C) If cracks are found as a result of the visual inspections required by paragraph (A) of this AD or an unacceptable electron beam weld is found as a result of ultrasonic inspection of paragraph (B) of this AD, before further flight replace the output gearshaft assembly with a like assembly which has been inspected and found to be acceptable in the electron beam weld area in accordance with the ultrasonic inspection technique described herein. (D) Output gearshaft assemblies ultrasonically inspected and found to have acceptable electron beam welds in the transmission output shaft are to be identified in accordance with Figure 2 of DN-105, or FAA approved equivalent. (E) Special flight permits may be issued in accordance with Parts 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections required by this AD. (F) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region, Hawthorne, California. This amendment becomes effective August 23, 1982.
2009-05-01: We are adopting a new airworthiness directive (AD) for the products listed above that will supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Inspection of a high time aircraft has revealed cracks in the Horizontal Stabiliser rear spar splice plate and inboard main ribs around the area of the Horizontal Stabiliser rear pivot attachment. Additionally, failure of some attach bolts in service may be due to improper assembly. This amendment is issued because the requirement document now contains an inspection for cracking in horizontal stabilisers which have load transferring fittings installed. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
81-15-51 R1: 81-15-51 R1 ROCKWELL: Amendment 39-4377. Applies to all Rockwell NA-265-60 airplanes modified in accordance with STC SA687NW and equipped with Lear Siegler Flap Actuation System, and all Rockwell NA-265-80 airplanes modified in accordance with STC SA847NW. To prevent improper flap motion caused by a failure in the flap actuation system, accomplish the following unless already accomplished: A. Within the next 20 landings following the effective date of this AD, or prior to the accumulation of 200 landings after incorporation of STC SA687NW or STC SA847NW, whichever comes later, rework the power drive unit and flap jackscrew actuators in accordance with paragraphs 1(a) and 1(b) of Rockwell International Sabreliner Service Bulletin 81-5, dated July 10, 1981. During rework of the flap jackscrew actuators, replace any drive shaft, part No. 57400-1640, found to have an extra hole with a new part that does not contain an extra hole. B. Repetitively, on or before every 200 landings following the accomplishment of paragraph (A.) above, remove and replace the power drive unit and flap jackscrew actuators in accordance with paragraphs 3(a) and 3(b) of Rockwell International Sabreliner Service Bulletin 81-5, Revision 1, dated December 15, 1981. Airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197 and FAR 21.199. Alternate means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 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 the addresses listed above. These documents may also be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective May 18, 1982 and was effective earlier to those recipients of Telegraph AD T81-15-51 dated July 9, 1981.
81-18-05: 81-18-05 GENERAL DYNAMICS: Amendment 39-4487. Applies to Model 240 and military models eligible or to be made eligible for civil use under Type Certificate A-793, and all such model airplanes converted to turbopropeller power, certificated in all categories. Compliance required as indicated, unless previously accomplished. To prevent structural failure of the wing structure, which could result from corrosion and cracking at the wing outer panel/wing center section joint, accomplish the following: (A) On or before September 15, 1981, and thereafter at intervals not to exceed 100 hours of additional time in service until compliance with the complete internal inspection required by paragraph (B) of this AD has been completed: 1) Conduct an external visual inspection of the wing in the area of the spar rails, both upper and lower, front and rear, from ten (10) inches inboard of bulkhead 15(WS323) to ten (10) inches outboard of bulkhead 17(WS346) in accordance with Figure 3 of General Dynamics 600 (240D) Service Bulletin No. 57-4A dated February 13, 1973, hereinafter referred to as S.B. No. 57-4A, for evidence of internal structural corrosion which may be indicated by some out-of-alignment or bulging of the external surface. If any indication of surface out-of-alignment, bulging, corrosion, cracks, or failed rivets is found, before further flight, conduct a complete internal inspection in accordance with paragraph (B) of this AD. 2) Conduct an internal visual inspection of the center wing to outer panel attach fittings upper and lower, front and rear, upper and lower bulkhead rails, and associated structure for corrosion and/or cracks as identified in S.B. No. 57-4A, Figures 1 through 3. This includes the structure at and between bulkheads 15(WS323) and 17(WS346). Remove all dirt from the corners, front and rear, and clear drain holes to allow for drainage of moisture. Access to this dry area is via the outer panel access door indicated on S.B. No. 57-4A, Figure 2. If any indication of surface out-of-alignment, bulging, failed rivets, corrosion, or cracks is found, before further flight, conduct the complete internal inspection in accordance with paragraph (B) of this AD. (B) On or before December 1, 1981, and thereafter at intervals not to exceed 3,000 hours of additional time in service or one year since the last such inspection, whichever occurs earlier: Conduct an internal visual inspection of the wing in accordance with S.B. 57-4A, paragraph 2, including spar rails (upper and lower, front and rear), center wing to outer panel attach fittings, upper and lower bulkhead rails, and associated structure for corrosion and/or cracks from bulkhead 14(WS300) to bulkhead 18(WS361), after cleaning all surfaces in accordance with the procedures shown in S.B. 57-4A, Figures 1 through 4. In addition to the visual inspection required above, using a dye penetrant method, inspect for cracks in spar rails and chordwise bulkhead tee rails, after removal of all dirt, paint, and integral fuel tank sealant, in the following areas at the specified stations. Upper and lower spar rails Six (6) inches spanwise inboard and outboard of bulkhead 15(WS323) and bulkhead 17(WS346) on the forward facing surface of the front spar rails and the aft facing surface of the rear spar rails. Upper and lower chordwise tee rails On the outboard facing surfaces at bulkhead 15(WS323) and the inboard facing surfaces at bulkhead 17(WS346) a minimum total of two (2) inches extending fore and aft chordwise from each of the forward and aft ends of the tee rails in the radius (or where the radius would exist prior to cut-out of a tee leg) in exposed areas accessible without fitting interference. Access to this "dry" wing area between bulkhead 15 and 17 is possible by removal of the outer panel access door indicated in S.B. 57-4A, Figure 2, page 5. The above dye penetrant inspections at bulkhead 17(WS346) are required only for those aircraft with integral fuel tanks installed in the wing outer panels outboard of bulkhead 17. (C) If corrosion or cracking is detected, repair in a manner approved by the Manager, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region, Hawthorne, California. (D) Military aircraft being converted for civil airworthiness certification and those civil aircraft which have been out of service for one year, shall, prior to further flight after the effective date of this AD, be inspected in accordance with paragraph (B) of this AD. (E) 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 required by this AD. (F) Alternate inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region, Hawthorne, California. (G) Reports of the discrepancies found are requested. The reports would provide surveillance of the propagation of fatigue cracking and corrosion in these aircraft. The reports should cite: airplane "N" number and serial number, nature of defect and part identification, total airplane operating hours, time since last inspection, and AD compliance paragraph. Forward reports to Manager, Western Aircraft Certification Field Office, FAA Northwest Mountain Region, 15000 Aviation Boulevard, Hawthorne, California 90261, by mail. This supersedes Amendment 39-4117, AD 81-11-08 (46 FR 28149). This Amendment 39-4487 becomes effective November 15, 1982, and was effective earlier to those recipients of priority mail AD 81-18-05 dated August 26, 1981.
90-07-04: 90-07-04 BRITISH AEROSPACE: Amendment 39-6554. Docket No. 89-NM-258-AD. Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent collapse of the nose landing gear, accomplish the following: A. Prior to the accumulation of 15,000 landings or within 150 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 15,000 landings, perform a dye penetrant or eddy current inspection of the lower faces of both lugs of the jack attachment arm on the nose landing gear housing over an area not less than 0.5 inch forward and aft of change in lug section, in accordance with British Aerospace Alert Service Bulletin 32-A-PM5946, Issue 1, dated April 6, 1987. B. If cracks are found, repair or replace with a serviceable part prior to further flight, in accordance with British Aerospace Alert Service Bulletin32-A-PM5946, Issue 1, dated April 6, 1987, 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, 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 MountainRegion, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6554, AD 90-07-04) becomes effective on April 30, 1990.
82-09-03: 82-09-03 BEECH: Amendment 39-4372. Applies to Model 77 (Serial Numbers WA-3 through WA-235, WA-237, WA-238, WA-240 through WA-254, WA-256, WA-258, WA-261 through WA-264, WA-266, WA-267 and WA-269) airplanes certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To detect any Beech P/N 108-440000-31 shoulder harness attach brackets which may have been improperly installed during manufacture or when complying with AD 81-09-05 and to ensure the required structural level of occupant protection during minor crash conditions, within the next 50 hours time-in-service after the effective date of this AD, accomplish the following: a) Visually inspect and, if required, replace the P/N 108-440000-31 shoulder harness attach bracket in accordance with procedures set forth in Beechcraft Service Instructions No. 1173, Rev. 1. If an undrilled P/N 108-440000-31U shoulder harness attach bracket was installed and minimum edge distances specifiedin Rev. 1, Figure 1, were maintained on the attaching screws and rivets when complying with AD 81-09-05, the bracket installation is acceptable. Make the prescribed entry in the aircraft maintenance records indicating compliance with this AD. b) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. c) Any equivalent method of compliance with this AD, if used, must be approved by the Chief, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 269- 7000. This amendment supersedes Amendment 39-4101 (AD 81-09-05) effective May 7, 1981. This amendment becomes effective on May 6, 1982.
2009-02-08: The FAA is superseding an existing airworthiness directive (AD) for Turbomeca Turmo IV A and IV C series turboshaft engines. That AD is applicable to engines with oil-tank-to-oil-cooler flexible lubrication pipes, part number (P/N) 0 249 92 813 0 or P/N 0 249 92 916 0, installed. That AD currently requires identifying, inspecting, and replacing affected flexible lubrication pipes manufactured after April 1, 2003. That AD also requires initial and repetitive borescope inspections of affected pipes, visual inspections for oil leakage, and visual inspections of the oil filter. That AD also requires that if both engines on the same helicopter each have an affected pipe, replacing one of the affected pipes before further flight. This AD does not contain that requirement. This AD requires the same inspections as the superseded AD and adds inspection of oil-pump-to-intermediate- bearing flexible lubricating pipe, P/N 0 249 92 808 0. This AD also requires all remaining affected flexible lubrication pipes, P/N 0 249 92 813 0, P/N 0 249 92 916 0, and P/N 0 249 92 808 to be replaced as terminating action to the repetitive inspections for those affected pipes. This AD results from additional shutdowns caused by pipes, P/N 0 249 92 808 0, and the introduction of Turbomeca Modifications TU 231 and TU 233 that replace pipes, P/N 0 249 92 813 0, P/N 0 249 92 916 0, and P/N 0 249 92 808. We are issuing this AD to prevent helicopter engine in-flight shutdown of one or both engines resulting in an emergency auto-rotation landing or accident.
87-17-08: 87-17-08 SHORT BROTHERS PLC: Amendment 39-5712. Applies to Model SD3-60 airplanes, serial numbers SH3601 through SH3678, certificated in any category. Compliance required as indicated, unless previously accomplished. To ensure that failure of the fuel purge valve cannot result in fuel ingress into the main cabin, accomplish the following: A. Within 90 days after the effective date of this AD, apply sealant to the fuselage top skin in accordance with the "Accomplishment Instructions," of Short Service Bulletin SD360- 53-22, Revision 1, dated April 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 modifications 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 Shorts Aircraft, 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 September 22, 1987.
2008-25-05: The FAA is superseding an existing airworthiness directive (AD), which applies to all McDonnell Douglas Model DC-8 airplanes. That AD currently requires, among other things, revision of an existing program of structural inspections. This new AD requires implementation of a revised program of structural inspections of baseline structure to detect and correct fatigue cracking in order to ensure the continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This new AD also reduces the inspection threshold for certain principal structural elements. This AD results from a significant number of these airplanes approaching or exceeding the design service goal on which the initial type certification approval was predicated. We are issuing this AD to detect and correct fatigue cracking that could compromise the structural integrity of these airplanes.
88-23-03: 88-23-03 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-6249. Final copy of priority letter AD. Applicability: All BHTI Model 206A, 206B, 206B-1, 206L, 206L-1, and 206L-3 helicopters certificated in any category, with tail rotor yoke assembly, P/N 206-011-819-101, identified with the following serial numbers: A - 2009 A - 2010 A - 2023 A - 2070 A - 2073 A - 2077 A - 2078 A - 2079 A - 2084 A - 2087 A - 2133 A - 2144 A - 2150 A - 2167 A - 2173 A - 2189 A - 2195 A - 2198 A - 2203 A - 2213 A - 2219 A - 2221 A - 2223 A - 2227 A - 2229 A - 2234 A - 226 A - 2243 A - 2262 Compliance: Required as indicated, unless already accomplished. To prevent the failure of the tail rotor yoke assembly, loss of the tail rotor blade, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, inspect the aircraft to determine the part number and serial number of the installed tail rotor yoke assembly. If P/N 206-011-819-101 with a serial number listed above is installed on the helicopter, remove and replace the assembly with an airworthy yoke assembly. (b) An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be used when approved by the Manager, Rotorcraft Certification Office, Rotorcraft Directorate, Aircraft Certification Service, FAA, Southwest Region. (c) In accordance with FAR 21.197 and 21.199, flight is permitted to a base where removal and replacement of the affected tail rotor yoke required by this AD may be accomplished. This amendment (39-6249, AD 88-23-03) becomes effective on July 25, 1989, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 88-23-03, issued November 15, 1988, which contained this amendment.
2008-26-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Several landing gear emergency extension valves have been found seized * * *. This condition, if not corrected, could result in malfunctioning of the landing gear release during an operational emergency. * * * * * This malfunction could cause failure of the landing gear to extend and lock in the extended position, which could result in a gear up landing and reduced controllability of the airplane on the ground. We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-26-05: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Occurrence of cracks in the exhaust muffler in the area of the exhaust bottom and exhaust flange were reported, which could lead to toxic contamination inside the cabin. We are issuing this AD to require actions to correct the unsafe condition on these products, which could result in carbon monoxide contamination in the cockpit, which can adversely affect the pilot, and possibly result in loss of control of the aircraft.
85-03-02: 85-03-02 ROLLADEN-SCHNEIDER FLUGZEUGBAU GmbH: Amendment 39-4996. Applies to Models LS4 and LS4a sailplanes, serial numbers up to 4340 inclusive, certificated in any category. Compliance is required prior to further flight, after the effective date of this AD, unless already accomplished. To prevent possible jamming of lower air brake blade, accomplish the following: (a) Assemble the sailplane. (b) With air brakes fully extended, measure overlap between the bottom edge of the lower blade of the air brake and wing skin lip. If the distance is less than five millimeters (0.2 inches), proceed according to subparagraph (c) below. If distance is greater than five millimeters, no further action is required. (c) (1) Retract air brakes until the overlap distance is at least five millimeters (0.2 inches) at both wing positions. (2) Measure extended height of the air brake at the inboard edge. If the distance is less than 150 millimeters (5.91 inches) contactthe manufacturer and incorporate any necessary modifications. (3) Install stop fitting P/N 4R6-15, using steel blind rivet (4mm dia. x 10mm lg.) on air brake pushrod in cockpit such that main bulkhead reduces travel to yield minimum overlap specified in paragraph (b). NOTE: Rolladen-Schneider TB No. 4020, dated September 1, 1983, applies to this AD. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium 09667-1011; telephone 513.38.30. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. This amendment becomes effective on February 25, 1985.
2008-24-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: During scheduled maintenance inspection, a bolt which connects the PCU (power control unit) to the elevator surface was found fractured in the assembly. Further inspection of the assembly revealed that the bearing on the PCU rod end had seized, which resulted in damage to the attachment fitting bushing and fracture of the bolt. Inspection of other in-service airplanes revealed two more seized PCU attachment joints. However, except seizure, no fractured bolt was found on these airplanes. Failure of the bolts in both PCUs on one side could result in disconnection of the elevator control surface which would lead to flutter and loss of the aircraft. * * ** * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2008-24-08: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800 and -900 series airplanes. This AD requires an inspection of the escape slides for the forward and aft entry and service doors to determine the part number and service bulletin number stenciled on the escape slide girt, and modification of the escape slide assemblies. This AD also requires concurrent modification of the escape slide latch assemblies; concurrent inspection of the escape slides to determine the part number and service bulletin number stenciled on the escape slide girts, and replacement of the trigger housing on the regulator valve with an improved trigger housing if necessary; and concurrent replacement of the rod in the pilot valve regulator with a new, improved rod; as applicable. This AD results from reports that certain escape slides did not automatically inflate when deployed or after the manual inflation cable was pulled. We are issuing this AD to preventfailure of an escape slide to inflate when deployed, which could result in the slide being unusable during an emergency evacuation and consequent injury to passengers or crewmembers.
83-26-03: 83-26-03 BF GOODRICH: Amendment 39-4811. Applies to the following aircraft tires: \n\n\t1.\t17.5x5.75-8, 12PR, 210MPH, P/N 038-627, S/N 3224A-XXXXX, and \n\n\t2.\t18x5.5, 10PR, 210MPH, P/N 033-631, S/N 3215A-XXXXX through 3217A-XXXXX. \n\n\tThese tires are eligible for, but not limited to use on, all Gates Learjet models and Fairchild Swearingen Model SA226-TC airplanes. \n\n\tCompliance: Required prior to next takeoff, unless already accomplished. \n\n\tTo avoid tread loss and possible subsequent tire failure, accomplish the following: \n\n\tRemove the applicable part number and serial number BF Goodrich tires from the aircraft and either destroy them or return them to BF Goodrich for destruction. Cutting the tire carcass is an approved means of destruction. \n\n\tNOTE: The serial numbers of the tires are interpreted as follows: \n\n\n\n\t\n\tThis amendment becomes effective on February 21, 1984, to all persons except those to whom it has already been made effective by priority letter from the FAA dated December 23, 1983, and is identified as AD 83-26-03.
85-03-07: 85-03-07 AIRBUS INDUSTRIE: Amendment 39-4999. Applies to Model A300 B2 and B4 series airplanes, serial numbers as listed in the Airbus Industrie Service Bulletin A300-28-039, Revision 2, dated December 17, 1981, certificated in all categories. To prevent rupture of the feeder fuel lines located inside the engine pylons, accomplish the following, unless previously accomplished: A. Prior to the accumulation of 4,000 hours total time in service or within the next 120 days after the effective date of this AD, whichever occurs later, install an additional clamp on the feeder fuel line located inside each engine pylon in accordance with the accomplishment instructions of the service bulletin. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, 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 inspections and/or modifications required by this AD. This amendment becomes effective March 11, 1985.
2008-22-09: We are adopting a new airworthiness directive (AD) for all Boeing Model 747SP series airplanes. This AD requires repetitive lubrication of the rudder tab hinges and repetitive replacement of the rudder tab control rods. This AD results from reports of freeplay- induced vibration on the control surfaces on Boeing Model 727, 737, 757, and 767 airplanes. We are issuing this AD to prevent damage to the control surface structure during flight, which could result in loss of control of the airplane.
2008-09-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. We are issuing this AD to require actionsto correct the unsafe condition on these products.
2008-22-24: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of installed low pressure compressor (LPC) fan blade roots on-wing and during overhaul, and relubrication according to accumulated life cycles. Also, that AD introduces application of Metco 58 blade root coating as an optional terminating action. This AD requires the same actions but adds compliance paragraphs to relax the compliance schedule for repetitive inspections for fan blades operating within RB211-535E4 flight profiles A and B, if certain requirements are met. This AD also relaxes the initial compliance threshold by extending the cycles at which an initial inspection is required. This AD results from RR issuing Mandatory Service Bulletin (MSB) No. RB.211-72-C879, Revision 5 and Revision 6, that introduced a relaxed repetitive compliance schedule for fan blades operating within RB211-535E4 flight profiles A and B, if certain requirements are met, and introduced a relaxed initial compliance threshold. We are issuing this AD to detect cracks in LPC fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
87-06-05: 87-06-05 MCDONNELL DOUGLAS: Amendment 39-5572. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes, certificated in any category, equipped with Aircraft Mechanics, Inc., crew seats model numbers, 1056, 1057, and 1058, having serial numbers 001 through 907 and 911. Compliance required as indicated, unless previously accomplished. \n\n\tTo preclude the potential of damage to crew seat life vests, accomplish the following: \n\n\tA.\tWithin 12 months after the effective date of this AD, inspect the life vest. If any signs of chafing are found, replace before further flight with a serviceable unit. \n\n\tB.\tWithin 12 months after the effective date of this AD, modify the crew seat in accordance with the accomplishment instructions of Aircraft Mechanics, Inc., Service Bulletin 25-DC-10/678-24, dated May 20, 1984, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.C.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial 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. \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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective April 2, 1987.
87-18-10: 87-18-10 INTREPRINDEREA DE CONSTRUCTII AERONAUTICE: Amendment 39- 5695. Applies to Model IS-28B2 gliders through serial number 160 inclusive certificated in any category. Compliance is required as indicated unless already accomplished. To prevent the failure of the aileron control levers and forks which could result in the glider becoming uncontrollable, accomplish the following: (a) Within the next 5 hours time-in-service after the effective date of this AD unless compliance with paragraph (c) has been accomplished, visually inspect the aileron control levers P/N 30AD.02.028 and aluminum NIA 181-2 forks using a 10 power or greater magnifying glass for cracks or deformation. (b) If a cracked or deformed part is found during the inspection required by paragraph (a) of this AD, before further flight, replace the aileron control levers and forks with serviceable levers and forks, new design P/N 30AD.02.028 lever and steel NIA 201-2 fork, in accordance with the accomplishment instructions of Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14, dated August 20, 1985. NOTE: The manufacturer has assigned the same part number to the new design aileron lever as the original design aileron lever. The new lever can be identified by measuring the length of the section which is reduced in thickness on the longer arm of the aileron lever. The new design aileron lever is reduced in thickness 42mm from the end of the longer arm whereas the old design aileron lever is reduced in thickness 27mm from the end of the longer arm. (c) Prior to September 30, 1987, replace any aileron control system levers and forks not replaced in accordance with paragraph (b) of this AD, with serviceable levers and forks, new design P/N 30AD.02.028 lever and steel NIA 201-2 fork, in accordance with Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14 dated August 20, 1985. NOTE: The aileron levers removed from service should be destroyed or disfigured to prevent reuse. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o American Embassy, 15 Rue de la Loi B-1040, Brussels, Belgium; telephone 513.38.30 ext. 2710, or the Manager, Federal Aviation Administration, New England Region, Aircraft Certification Division, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone 516-791-6680. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14, dated August 20, 1985, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Sprague Aviation Incorporated, 699 Linwood, Vacaville, California 95688. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, Rules Docket 87-ANE-01 between the hours of 8:00 a.m. and 4:30 p.m.; Monday thru Friday, except federal holidays. This amendment becomes effective on September 3, 1987.
89-20-01 R1: 89-20-01 R1 GENERAL ELECTRIC COMPANY: Amendment 39-6337 as revised by Amendment 39-6411. Applicability: General Electric Company (GE) CF6-6 series turbofan engines installed in McDonnell Douglas DC10-10 aircraft. Compliance: Required as indicated, unless already accomplished. To detect the existence of metallurgical imperfections in Stage 1 fan disks which could adversely affect Stage 1 fan disk service life, ultrasonic inspect all Stage 1 fan disks in accordance with the Appendix to this AD, and the following schedule: (a) All Stage 1 fan disks with those serial numbers listed in TABLE 1 of this AD, immersion ultrasonic inspect no later than October 27, 1989. (b) All Stage 1 fan disks identified by those serial numbers listed in TABLE 2 of this AD, as follows: (1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than November 21, 1989. (2) Immersion ultrasonic inspect within the next 500 cycles in service after accomplishing the contact ultrasonic inspection requirements of paragraph (b)(1) above, or at the next shop visit after October 7, 1989, or no later than April 1, 1990, whichever comes first. (c) All Stage 1 fan disks identified by serial numbers listed in TABLE 3 of this AD, as follows: (1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than February 4, 1990, and reinspect at intervals not to exceed 500 cycles since the last contact ultrasonic inspection until the immersion ultrasonic requirement of paragraph (c)(2) has been accomplished. (2) Immersion ultrasonic inspect at the next shop visit after October 7, 1989, but no later than December 31, 1990. (d) All Stage 1 fan disks identified by those serial numbers listed in TABLE 2A of this AD, as follows: (1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than January 23, 1990. (2) Immersion ultrasonic inspect within the next 500 cycles in service after accomplishing the contact ultrasonic inspection requirements of paragraph (d)(1) above, or at the next shop visit after December 12, 1989, or no later than June 5, 1990, whichever comes first. (e) All Stage 1 fan disks identified by serial numbers listed in TABLE 3A of this AD, as follows: (1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than April 10, 1990, and reinspect at intervals not to exceed 500 cycles since the last contact ultrasonic inspection until the immersion ultrasonic requirement of paragraph (e)(2) has been accomplished. (2) Immersion ultrasonic inspect at the next shop visit after December 12, 1989, but no later than March 5, 1991. NOTES: (1) Disks which have been previously immersion ultrasonic inspected in accordance with GE Commercial Engine Memorandum No. 98, Rev. 2, dated October 5, 1989, are considered to be in compliance with the immersion ultrasonic inspection requirements of paragraphs (a), (b), (c), (d), and (e) above. (2) For the purpose of this AD, "shop visit" is defined as the induction of the engine into the shop for any reason. (3) Accomplishment of the immersion ultrasonic inspection requirements of paragraphs (b)(2), (c)(2), (d)(2), and (e)(2) above relieves the requirements for contact ultrasonic inspections of paragraphs (b)(1), (c)(1), (d)(1), and (e)(1) above. (f) Remove from service, prior to further flight, fan disks inspected in accordance with paragraphs (a), (b), (c), (d), and (e) which do not meet the acceptance criteria of the Appendix to this AD and replace with a serviceable part. Report all inspection findings in writing within 10 days of the inspection to the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts, 01803; Telex No. 949301 FAANE BURL. Information collection requirements contained in this regulation (Section 39.13) have been approved by the Office of Management and Budget under the provisions of the Paperwork Reduction Act of 1980 (Pub. L. 96- 511) and have been assigned OMB Control Number 2120-0056. (g) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (h) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedules specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. TABLE 1 MP000382 MP000383 MP000384 MP000386 MP000387 MP000388 TABLE 2 MP000352 MP000363 MP000374 MP000390 MP000407 MP0A0117 MP000354 MP000364 MP000375 MP000393 MP000411 MP0A0133 MP000357 MP000365 MP000376 MP000395 MP0A0108 MP0A0136 MP000358 MP000368 MP000377 MP000397 MP0A0109 MP0A0140 MP000359 MP000370 MP000378 MP000398 MP0A0110 MP0A0141 MP000360 MP000371 MP000379 MP000399 MP0A0111 MP0A0142 MP000361 MP000372 MP000380 MP000402 MP0A0112 MP0A0143 MP000362 MP000373 MP000389 MP000404 MP0A0113 MP0A0145 MP0A0115 TABLE 2A MP0A0135 MP0A0182 TABLE 3 MP000150 MP000188 MP000222 MP000251 MP000284 MP000319 MP000151 MP000189 MP000223 MP000253 MP000285 MP000320 MP000152 MP000190 MP000224 MP000254 MP000286 MP000321 MP000153 MP000191 MP000225 MP000255 MP000289 MP000322 MP000154 MP000193 MP000226 MP000257 MP000290 MP000323 MP000155 MP000194 MP000228 MP000258 MP000291 MP000325 MP000156 MP000195 MP000229 MP000260 MP000292 MP000326 MP000158 MP000196 MP000230 MP000263 MP000293 MP000331 MP000159 MP000197 MP000231 MP000264 MP000295 MP000334 MP000160 MP000198 MP000232 MP000265 MP000297 MP000336 MP000161 MP000199 MP000233 MP000266 MP000298 MP000337 MP000162 MP000200 MP000234 MP000267 MP000299 MP000338 MP000163 MP000204 MP000235 MP000268 MP000300 MP000339 MP000168 MP000205 MP000236 MP000270 MP000302 MP000340 MP000171 MP000206 MP000237 MP000271 MP000303 MP000341 MP000172 MP000207 MP000238 MP000272 MP000304 MP000342 MP000173 MP000208 MP000240 MP000273 MP000305 MP000343 MP000175 MP000209 MP000241 MP000274 MP000308 MP000346 MP000177 MP000212 MP000243 MP000276 MP000311 MP000348 MP000178 MP000213 MP000244 MP000277 MP000312 MP000349 MP000179 MP000214 MP000245 MP000278 MP000313 MP000350 MP000180 MP000215 MP000246 MP000279 MP000314 MP0A0137 MP000181 MP000216 MP000247 MP000280 MP000315 MP0A0139 MP000182 MP000217 MP000248 MP000281 MP000316 MP0A0207 MP000184 MP000218 MP000249 MP000282 MP000317 MP0A0439 MP000185 MP000219 MP000250 MP000283 MP000318 MP000186 MP000220 MP000187 MP000221 TABLE 3A MP000618 MP000139 MP000103 MP000011 MP0C2744 MP0A0376 MP000436 MPOOO136 MP000102 MP000010 MP0C0321 MP0A0291 MP000353 MP000113 MP000078 MP000009 MP0A0880 MP0A0284 MP000351 MP000111 MP000016 MP000005 MP0A0810 MP0A0206 MP000294 MP000109 MP000015 MP000004 MP0A0801 MP0A0200 MP000174 MP000108 MP000014 MP000003 MP0A0736 MP0A0139 MP000149 MP000107 MP000013 MP000002 MP0A0662 MP0A0138 MP000141 MP000104 MP000012 MP0H3844 MP0A0481 MP0G2753 The ultrasonic inspections shall be done in accordance with the Appendix to this AD. This AD revises Amendment 39-6337 (54 FR 38814; September 21, 1989), AD 89-20-01, which became effective on October 7, 1989. This amendment (39-6411, AD 89-20-01 R1) becomes effective on December 12, 1989. 89-20-01 R1 Appendix The applicable General Electric Service Bulletin (CF6-6) 72-947, Revision 2, dated November 21, 1989, and the following General Electric Manufacturing and Field Quality Procedures may be obtained from General Electric Company, Technical Publications Department, 1 Neuman Way, Cincinnati, Ohio 45215, or may be examined in the Regional Rules Docket (Docket #89-ANE-35), FAA, New England Region, Office of Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803. (A) General Electric Manufacturing and Field Quality Technology Procedure No. 391, issued September 15, 1989, Rev. 1, dated September 28, 1989. (B) General Electric Manufacturing and Field Quality Technology Procedure No. 384, issued September 15, 1989, Rev. 2, dated October 5, 1989. (C) General Electric Manufacturing and Field Quality Technology Procedure No. 385, issued September 14, 1989, Rev. 2, dated October 5, 1989. (D) General Electric Manufacturing and Field Quality Technology Procedure No. 389, issued September 14, 1989, Rev. 2, dated October 3, 1989.
2008-22-02: We are adopting a new airworthiness directive (AD) for Maryland Air Industries, Inc., Model Fairchild F-27 and FH-227 Series Airplanes. This AD requires operators to modify their airplanes and revise their inspection or maintenance programs to incorporate instructions for maintenance and inspection of the fuel tank systems, as appropriate, by December 16, 2008, using information developed in accordance with Special Federal Aviation Regulation 88 (SFAR 88). This AD results from fuel system safety reviews done on similar airplane models in accordance with SFAR 88. These safety reviews identified potential unsafe conditions on Model Fairchild F-27 and FH-227 series airplanes for which the type certificate holder, Maryland Air Industries, Inc., has not conducted SFAR 88 safety reviews, has not provided corrective actions, and does not plan to do so. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2000-23-06: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires replacement of defective hydraulic tubing in the left and right wings with new hydraulic tubing. 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 loss of hydraulic pressure which could result in reduced controllability of the airplane.