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84-07-03 R1: 84-07-03 R1 BRITISH AEROSPACE, AIRCRAFT GROUP: Amendment 39-4837 as amended by Amendment 39-5251. Applies to all Viscount Model 700 series and 800 series airplanes certificated in all categories. Compliance required as indicated. To prevent collapse of the nose landing gear, accomplish the following: 1. Within the next six months after the effective date of this AD, unless previously accomplished within the last six months, and thereafter at intervals not to exceed six months, inspect and repair, as necessary, the nose landing gear in accordance with Paragraph 2, Accomplishment Instructions, of British Aerospace Preliminary Technical Leaflet No. 125, Issue 4, for all Model 800 series airplanes. Paragraphs 2.5 and 2.5.1 must be accomplished at the first inspection and thereafter at intervals not to exceed one year. 2. Within the next six months after the effective date of this AD, unless previously accomplished within the last six months, and thereafter at intervals not to exceed six months, inspect and repair, as necessary, the nose landing gear in accordance with the Accomplishment Instructions of Paragraphs 2.1 thru 2.4, and 2.7 of the British Aerospace Preliminary Technical Leaflet No. 262, Issue 4, for all Model 700 series airplanes; and during the first inspection only, accomplish Paragraph 2.6 and BA Modification D.3284, if applicable. Paragraph 2.5 must be accomplished at the first inspection and thereafter at intervals not to exceed one year. 3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 4. 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. Amendment 39-4837 supersedes Amendment 39-1058 (35 FR 12325), AD 70-16-06. Amendment 39-4837 becameeffective May 6, 1984. This Amendment 39-5251 becomes effective March 24, 1986.
99-11-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time detailed visual inspection to detect improperly installed or frayed aileron cables, and a one-time detailed visual inspection to detect improper identification or location of the cable markers, and corrective actions, if necessary. This amendment is prompted by a report that an aileron cable failed, due to improper installation onto the wrong groove of an aileron cable drum. The actions specified by this AD are intended to detect and correct an improperly installed aileron cable; such installation could lead to the failure of the aileron cable, and consequent reduced lateral control capability of the airplane.
99-11-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that requires repetitive inspections to ensure proper installation of the engine thrust link components, and follow-on corrective action, if necessary; and replacement of the forward engine mount end cap assembly with an improved end cap assembly. Such replacement, when accomplished, will terminate the repetitive inspections. This amendment is prompted by a report of fatigue cracking of end cap bolts, caused by improper installation. Subsequent investigation revealed that properly installed end caps also are subject to early fatigue cracking. The actions specified by this AD are intended to prevent failure of the end cap assembly, which could lead to separation of the engine from the airplane in the event of a primary thrust linkage failure.
2006-05-05: The FAA is adopting a new airworthiness directive (AD) for certain MT-Propeller Entwicklung GmbH variable pitch and fixed pitch propellers with serial numbers (SNs) below 95000, which have not been overhauled since April 1994. This AD requires overhauling the propeller blades of these propellers within 30 days after the effective date of the AD. This AD also requires performing initial and repetitive visual inspections of affected propeller blades. This AD also requires removing all propeller blades from service with damaged erosion sheath bonding or loose erosion sheaths and installing any missing or damaged polyurethane protective strips. This AD results from reports of stainless steel leading edge erosion sheaths separating from propeller blades and reports of propeller blades with damaged or missing polyurethane protective strips (PU-protection tape) due to insufficient inspection procedures in older MT-Propeller Entwicklung GmbH Operation & Installation Manuals. We are issuing this AD to prevent erosion sheath separation leading to damage of the airplane.
81-10-10 R1: 81-10-10 R1 MCDONNELL DOUGLAS: Amendment 39-4116 as amended by Amendment 39-4629. Applies to all McDonnell Douglas Model DC-9 series and Military C-9 series airplanes, certificated in all categories. Compliance required as prescribed herein. To prevent fatigue cracking and possible structural failure of the forward galley service doors, P/N 5910084 and P/N 5910538, on airplanes with 12,000 or more landings accumulated on and after the effective date of this AD, accomplish the following: \n\n\tA.\tWithin the next 30 days after the effective date of this amendment, unless accomplished within the last 3,100 landings, perform an operational check of the door, and a visual inspection for general condition of door, pan and seals, door stops, and set screws. If corrective actions are deemed necessary, accomplish rework and/or replacement per operator's approved maintenance program. \n\n\tNOTE: Removal of seals and liner not required to perform this inspection. \n\n\tB.\tIn accordance withthe schedule below, perform a close visual inspection of the door pan, forward and aft ends of horizontal beams (frames), including the bend radius along the upper and lower flanges, tee fittings and clips, or inspect in accordance with McDonnell Douglas DC-9 Service Bulletins 52-125 dated August 11, 1981, or 52-127 dated January 10, 1983, as applicable. \n\n\tNOTE: Removal of seals is not required to perform this inspection. \n\n\t\t1.\tInitial visual inspection schedule (unless accomplished within the last 3,100 landings): \n\n\n Accumulated Landings\n(on effective date of this AD)\nInitial Inspection\n (from effective date of this AD) \n12,000 - 14,999\t\n4,000 landings\n15,000 - 19,999\t\n2,900 landings \n20,000 - 24,999\t\n1,800 landings \n 25,000 and over\t\n 900 landings \n \t\t\t\n\n\tNOTE: If the total number of landings cannot be determined for a particular door, for the purpose of this AD it must be assumed the door has 25,000 or more landings. \n\n\t\t2.\tRepeat the inspections specified in paragraph B.1., above, at intervals not to exceed 4,000 landings from the last inspection until terminating action specified in paragraph C., below, is accomplished. \n\n\t\t3.\tFor airplanes with less than 12,000 landings on the effective date of this AD, inspect in accordance with paragraph B., above, before the accumulation of 16,000 landings. \n\n\t\t4.\tIf no cracks are found, continue repetitive inspections per paragraph B.2., above, until terminating actions specified in paragraph C.1., below, is accomplished. \n\n\t\t5.\tIf cracks are found, install applicable repairs on cracked pan and/or beams and accomplish repetitive inspections per paragraph B.2., above, until terminating action specified in paragraph C.2., below, is accomplished. For Part Numbers 5910084-(***) and 5910538-(***), with cracks which exceed the limits defined in Douglas Service Rework Drawing 5939988 or J060167, respectively, the affected beam(s) must be replaced with new like beam(s) prior to installing preventative repairs. \n\n\t(NOTE: *** denotes any configuration.) \n\n\t\t6.\tPrevious accomplishment of preventative repairs, required by this AD, which are outlined in McDonnell Douglas Service Rework Drawing 5939988, may be considered as equivalent methods for complying with the requirements of this AD. \n\n\tC.\tTerminating Action: The following constitutes terminating action for this AD: \n\n\t\t1.\tFor aircraft found to be crack free, accomplish the applicable preventative repair per Paragraph 2, Accomplishment Instructions specified in McDonnell Douglas DC-9 Service Bulletins 52-125 dated August 11, 1982, or 52-127 dated January 10, 1983, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\t2.\tFor aircraft found to have cracks, accomplish the applicable repairs and inspections and install preventative repairs per paragraph 2, Accomplishment Instructions, specified in McDonnell Douglas DC-9 Service Bulletins 52-125 dated August 11, 1982, or 52-127 dated January 10, 1983, or later revisions 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 FARs 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tE.\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the change for that operator. \n\n\tF.\tFor the purposes of complying with this AD, subject to the acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hours time in service by the operator's fleet average time from takeoff to landing. \n\n\tG.\tAlternative inspections, repairs, or other actions accomplished on or after the effective date of this AD, which provide an equivalent level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received these 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, C1-750 (54-60). These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tAmendment 39-4116 became effective May 28, 1981. \n\n\tThis Amendment 39-4629 becomes effective April 20, 1983.
2019-25-16: The FAA is superseding Airworthiness Directive (AD) 2017-06- 08, which applied to certain Embraer S.A. Model ERJ 170-100 LR, -100 STD, -100 SE, and -100 SU airplanes; and Model ERJ 170-200 LR, -200 SU, and -200 STD airplanes. AD 2017-06-08 required revising the existing maintenance or inspection program, as applicable, to incorporate more restrictive airworthiness limitations. This AD continues to require that revision; adds a new requirement for revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; and adds airplanes to the applicability. Since the FAA issued AD 2017-06-08, the agency determined that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2009-15-17: 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: * * * * * [B]ogie beam internal paint has been degraded, leading to a loss of cadmium plating and thus allowing development of corrosion pitting. If not corrected, this situation under higher speed could result in the aircraft departing the runway or in the bogie [beam] detaching from the aircraft or [main landing] gear collapses, which would constitute an unsafe condition. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
99-11-09: 99-11-09 Pratt & Whitney: Amendment 39-11180. Docket No. 94-ANE-54. Supersedes AD 94-26-06, Amendment 39-9102. Applicability: Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 series turbofan engines, installed on but not limited to Airbus A300 series, Boeing 747 series, and McDonnell Douglas DC-10 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent diffuser case rupture, an uncontained engine failure, and damage to the aircraft, accomplish the following: (a) Perform initial and repetitive fluorescent penetrant inspections (FPI) or eddy current inspections (ECI) of diffuser case rear rails for cracks in accordance with the Accomplishment Instructions of PW JT9D (SB) No. 5749, Revision 8, dated October 30, 1998, as follows: (1) For engines on-wing that have not had the diffuser case rear rail FPI or ECI inspected using the procedures referenced in PW JT9D SB No. 5749, Revision 4, dated May 10, 1993; Revision 5, dated September 29, 1995; Revision 6, dated May 8, 1998; Revision 7, dated August 19, 1998; or Revision 8, dated October 30, 1998; Section 2, Part 1 A (1)-(3), accomplish the following: (i) Perform an initial on-wing inspection within 25 cycles ofthe effective date of this AD in accordance with Section 2, Part 2 of PW JT9D SB No. 5749, Revision 8, dated October 30, 1998. (ii) Thereafter, except as provided in paragraph (a)(4) of this AD, perform on-wing inspections in accordance with the time requirements listed in Section 2, Part 2 of PW JT9D SB No. 5749, Revision 8, dated October 30, 1998. (2) For engines on-wing that have had the diffuser case rear rail FPI or ECI inspected using the procedures referenced in PW JT9D SB No. 5749, Revision 4, dated May 10, 1999; Revision 5, dated September 29, 1995; Revision 6, dated May 8, 1998; Revision 7, dated August 19, 1998; or Revision 8, dated October 30, 1998; Section 2, Part 1 A (1)-(3), perform initial and repetitive on-wing inspections in accordance with PW JT9D SB 5749, Revision 8, dated October 30, 1998, within the time requirements listed in Section 2, Part 2 of that SB, except as provided in paragraph (a) (4) of this AD. (3) Remove from service diffuser cases thatdo not meet the return to service criteria stated in PW JT9D SB No. 5749, Revision 8, dated October 30, 1998, Section 2, Part 2 D, and replace with serviceable parts. (4) For engines that are overdue for an inspection on the effective date of this AD, accomplish the required inspection within 25 cycles in service of the effective date of this AD. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) Special flight permits may be issued in accordance with sections 21.197and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) The actions required by this AD shall be accomplished in accordance with the following Pratt & Whitney SB: Document No Pages Revision Date 5749 1, 2 8 October 30, 1998 3 6 May 8, 1998 4 7 August 19, 1998 5-7 6 May 8, 1998 8, 9 8 October 30, 1998 10, 11 6 May 8, 1998 12 7 August 19, 1998 13-18 6 May 8, 1998 Total pages: 18 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 Pratt & Whitney, Publication Department, Supervisor Technical Publications Distribution, M/S 132-30, 400 Main St., East Hartford, CT 06108; telephone (860) 565-7700, fax (860) 565-4503. Copies may be inspected at the FAA, New England Region, Office ofRegional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on July 26, 1999.
78-23-06: 78-23-06 MCDONNELL DOUGLAS: Amendment 39-3343. Applies to McDonnell Douglas DC-9-10, -20, -30, -40, -50 series airplanes, including the military versions, all serial numbers, certificated in all categories. \n\n\tCompliance is required within one year after the effective date of this AD. \n\n\tTo reduce the probability of an unnecessary rejected takeoff due to a false stall warning just after initiation of rotation, modify the stall warning system by extending the time delay to four seconds between nose gear lift-off and the initiation of stall warning, by accomplishing the following: \n\n\t(a)\tModify the stall warning circuitry in accordance with McDonnell Douglas DC-9 Service Bulletin 34-131 dated January 10, 1978. \n\n\tNOTE: Service Bulletin 34-131 dated January 10, 1978, is the only version of this service bulletin suitable for compliance with paragraph (a) of this AD. \n\n\t(b)\tEquivalent modifications, procedures, or revisions may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to a base for accomplishment of the modification required by this AD. \n\n\tThis amendment becomes effective December 11, 1978.
2006-04-15: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Artouste III B, Artouste III B1, and Artouste III D turboshaft engines. This AD requires removing certain fuel pumps from service and installing serviceable fuel pumps. This AD results from a report that an acceptance test facility used test equipment that was out of calibration, on certain fuel pumps, and those fuel pumps might have been accepted with a limitation in the maximum available fuel flow. We are issuing this AD to prevent reduced helicopter performance, subsequent loss of control of the helicopter, or accident.