Results
83-20-01: 83-20-01 GARLICK HELICOPTERS, HAWKINS & POWERS AVIATION, INC., WILCO AVIATION (BELL) MODEL UH-1B HELICOPTERS: Amendment 39-4731. Applies to Garlick Helicopters, Hawkins & Powers Aviation, Inc., and Wilco Aviation (Bell) UH-1B helicopters certified in all categories. Compliance is required within the next 100 hours time in service after the effective date of this AD unless already accomplished. To prevent excessive structural loads which could lead to mechanical failure and possible loss of a helicopter, accomplish the following: (a) Inspect the tail rotor hub assembly and identify the part number of the tail rotor hub assembly. The tail rotor hub assembly part number is located on the yoke assembly. (b) If the tail rotor hub assembly, P/N 204-011-801-003, is installed, remove and replace with P/N 204-011-801-005, 009, or 017. (c) Any equivalent method of compliance with paragraph (b) above of this AD must be approved by the Manager, Aircraft CertificationDivision, Southwest Region, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101. (d) In accordance with FAR 21.197, flight is permitted to a base where the inspections required by this AD may be accomplished. This amendment becomes effective November 1, 1983.
2005-22-03: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) (formerly Allison Engine Company) 501- D22A, 501-D22C, and 501-D22G turboprop engines. This AD requires a onetime inspection for proper metal hardness of certain 1st stage, 2nd stage, 3rd stage, and 4th stage turbine wheels. This AD results from a report of a turbine wheel found to be over dimensional limits, caused by improper metal hardness. We are issuing this AD to prevent uncontained turbine wheel failure, leading to damage of the airplane and total loss of engine power.
98-13-32: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that requires interim inspections to detect discrepancies of the main fitting subassembly of the main landing gear, and follow-on corrective actions, if necessary. This amendment also requires a one-time inspection to detect discrepancies of the fitting, repair of the fitting, if necessary, and application of new surface protection on the fitting, which would terminate the interim inspections. 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 cracking of the main fitting subassembly of the main landing gear, which could result in collapse of the main landing gear.
2005-21-06: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive inspections of the aft pressure bulkhead web for fatigue cracks, crack indications, discrepant holes, and corrosion; and repair if necessary. This AD results from reports of fatigue cracks in the aft pressure bulkhead web. We are issuing this AD to detect and correct such fatigue cracks, which could result in a rapid decompression of the airplane.
86-10-06: 86-10-06 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-5303. Applies to all BAe Model HS 748 airplanes, certificated in any category. Compliance is required within 60 days after the effective date of this AD. To prevent the overwing escape hatches from opening and becoming detached during flight, accomplish the following, unless already accomplished: A. Modify the overwing escape hatches in accordance with BAe Service Bulletin 52/115, dated July 4, 1984. 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 inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate documentfrom the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian, 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 June 16, 1986.
63-21-03: 63-21-03 HILLER: Amdt. 631 Part 507 Federal Register October 15, 1963. Applies to Models UH-12D and UH-12E Helicopters. Compliance required as indicated. Due to fatigue cracking and brazed doubler separation of main rotor blade, Parsons P/N's 2253-1101-02 and 2253-1101-03, inspect the top and bottom surfaces of each blade after removing paint in the area adjacent to the outboard end of the steel doubler brazed to the leading edge spar (approximately 27 inches from the blade root end), for doubler separation and for cracks in the leading edge spar near the end of the doubler as follows: (a) For all main rotor blades, conduct a visual inspection of the affected areas with a 4 to 6-power magnifying glass within 10 hours' time in service from the effective date of this AD and daily thereafter. When inspecting for cracks or separation in the lower surface, the blade tip must be supported in a manner to remove all droop from the blade. (b) For all main rotor blades, conduct a dye penetrant inspection of the affected areas within the next 10 hours' time in service after October 15, 1963, and thereafter at intervals not to exceed 25 hours' time in service from the last dye penetrant inspection for blades, Serial Number 1269 and below, and at intervals not to exceed 100 hours' time in service from the last dye penetrant inspection for blades, Serial Number 1270 and above. (c) In the event of any unusual main rotor vibration that cannot be corrected by normal tracking, balancing or rigging procedures, conduct a dye penetrant inspection of the affected areas. In addition, inspect for cracks the bolt hole and adjacent milled surfaces of the main rotor blade fork P/N 52110-3 by means of a dye penetrant inspection or FAA approved equivalent. For this inspection remove nut, washer and pin. Replace cracked forks before further flight. (d) Main rotor blades with cracks or doubler separation must be removed from service before further flight. (e) The repetitive visual and dye penetrant inspections required by this AD may be discontinued after the installation of blades. Parsons P/N 2253-1101-04. (Hiller Service Information Letter No. 3037A covers this subject.) This supersedes AD 60-17-02. This directive effective October 15, 1963. Revised April 8, 1966.
98-13-36: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A, SAAB 340B, and SAAB 2000 series airplanes, that requires repetitive operational tests of the pitch trim system of the elevator trim-tab of the flight control unit to ensure that the system operates correctly, and repair if necessary. This amendment is prompted by a report of uncommanded movement of the right-hand elevator trim-tab to a maximum deflection position, which was apparently due to a failure in the aircraft harness and a fault in the pitch trim synchronizer. The actions specified by this AD are intended to prevent such uncommanded movement of the elevator trim-tab, which could lead to structural overload of the horizontal stabilizers at speeds above 180 knots, and consequent reduced controllability of the airplane.
61-03-05: 61-03-05 LUSCOMBE: Amdt. 248 Part 507 Federal Register February 7, 1961. Applies to All Model 8 Series Aircraft Incorporating Wing Fuel Tanks. Compliance required as indicated. Within 50 hours' time in service after the effective date of this directive, remove the fairing at the wing root of each wing and inspect the wing root area for interference between the forward fuel line and the aileron cable and/or aileron pulley. Remove the trim panel over the forward door post and inspect the forward door post area for interference between the forward fuel line and the aileron cable and/or pulley. If any interference is found, bend fuel line sufficiently to provide the necessary clearance. Replace any worn fuel lines being careful to provide clearance when installing the replacement fuel line. This directive effective March 9, 1961.
2017-18-13: We are superseding Airworthiness Directive (AD) 2015-22-51 for Agusta S.p.A. (Agusta) Model A109A and A109A II helicopters. AD 2015- 22-51 required pre-flight checking and inspecting each main rotor blade (blade) for a crack and replacing any cracked blade. This new AD removes the check and requires inspecting each blade more frequently. This AD is prompted by a crack that was not detected during any of the pre-flight checks. The actions of this AD are intended to address the unsafe condition on these products.
2017-16-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of failure of an aft hinge bolt assembly in the nose landing gear (NLG) aft doors. This AD requires replacement of the aft hinge bolt assembly in the left and right NLG aft doors, with new aft hinge bolt assemblies. We are issuing this AD to address the unsafe condition on these products.
2005-21-01: This amendment supersedes an existing airworthiness directive (AD) that applies to Pratt & Whitney (PW) JT8D-200 series turbofan engines. That AD currently requires installing and periodically inspecting individual or sets of certain part number (P/N) temperature indicators on the No. 4 and 5 bearing compartment scavenge oil tube and performance of any necessary corrective action. This AD requires installing and periodically inspecting two temperature indicators on all PW JT8D-200 series turbofan engines, including those incorporating high pressure turbine (HPT) containment hardware. This AD results from five uncontained HPT shaft failures. We are issuing this AD to prevent oil fires and the resulting fracture of the HPT shaft which can result in uncontained release of engine fragments; engine fire; in-flight engine shutdown; and possible airplane damage.
98-13-13: This amendment adopts a new airworthiness directive (AD), applicable to all Mitsubishi Model YS-11 and YS-11A series airplanes. This amendment requires revising the Airplane Flight Manual (AFM) to prohibit positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller beta was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
2017-16-08: We are superseding Airworthiness Directive (AD) 2012-23-09, which applied to all Embraer S.A. Model ERJ 190-100 STD, -100 LR, and - 100 IGW airplanes; and Model ERJ 190-200 STD, -200 LR, and -200 IGW airplanes. AD 2012-23-09 required revising the maintenance program to incorporate certain modifications in airworthiness limitations. This new AD requires revising the maintenance or inspection program to incorporate certain modifications in the airworthiness limitations to include new inspection tasks and their respective thresholds and intervals. This AD was prompted by our determination that more restrictive maintenance requirements and airworthiness limitations are necessary. We are issuing this AD to address the unsafe condition on these products.
2005-21-04: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron (Bell) Model 47D1, 47G, 47G-2, 47G-2A, 47G-2A- 1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A and Coastal Helicopters, Inc. Model OH-13H (Tomcat Mark 5A, 6B, 6C) helicopters that have a certain scissors assembly or weld assembly scissors bracket installed. The AD requires, within 60 days, determining and recording the total hours time-in-service (TIS) for each Parts Manufacturer Approval (PMA)-produced scissors assembly and weld assembly scissors bracket and establishes a life limit for each affected part. This amendment is prompted by the need to establish a life limit on scissors assemblies and weld assembly scissors brackets produced under PMA No. PQ808SW or installed per Supplemental Type Certificate (STC) No. SH2772SW. The actions specified by this AD are intended to establish a life limit to prevent using a scissors assembly or weld assembly scissors bracket past it's life limit, which could result in failure of the part and subsequent loss of control of the helicopter.
76-08-03: 76-08-03 SCOTTISH AVIATION LTD. (Beagle Aircraft Ltd.): Amendment 39-2580. Applies to Model B-121 "PUP," Series 1, 2, and 3 airplanes, certificated in all categories. Compliance is required as indicated. To prevent a failure of the flap actuating lever and the consequent loss of airplane control, accomplish the following: (a) For airplanes with less than 400 hours total time in service on the effective date of this AD, comply with paragraph (d) of this AD within the next 25 hours time in service after the effective date of this AD or before the accumulation of 400 hours total time in service, whichever occurs later, unless already accomplished. Repeat the inspection required by paragraph (d) of this AD before the accumulation of 800 hours total time in service and, thereafter, at intervals not to exceed 100 hours time in service from the last inspection. (b) For airplanes with 400 or more hours total time in service but less than 800 hours total time in serviceon the effective date of this AD, comply with paragraph (d) of this AD within the next 25 hours time in service after the effective date of this AD, unless already accomplished. Repeat the inspection required by paragraph (d) of this AD before the accumulation of 800 hours total time in service, unless already accomplished within the previous 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection. (c) For airplanes with 800 or more total time in service on the effective date of this AD, comply with paragraph (d) of this AD within the next 25 hours time in service, after the effective date of this AD unless already accomplished within the previous 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection. (d) Comply with the following: (1) Remove wing root fillets to gain access to the flap actuating lever assemblies. (2) Remove split pins,nuts, washers and bolts that attach the flap actuating rods to the port and starboard flap actuating lever assemblies. (3) Inspect the flap actuating lever assemblies. P/N's BE.45.10181/9 (port) and BE.45.10181/15 (starboard) for cracks, using a dye-penetrant method, or an FAA-approved equivalent means. (NOTE: During the inspections conducted in accordance with paragraph (d)(3) of this AD particular attention should be directed to the actuating rod attachment boss). (4) If a cracks is found in any part of the flap actuating lever assembly as a result of any inspection required by this AD, before further flight, replace the cracked part with a new part of the same part number, or an FAA-approved equivalent, and continue to inspect the flap actuating lever assemblies in accordance with paragraph (d) of this AD at the intervals established in paragraph (a), (b) or (c) of this AD, as applicable. (5) Re-attach the flap actuating rods to the flap actuating lever assemblies using new split pins. (6) Re-rig flaps. (7) Re-install wing root fillets. (8) Perform a functional check of the flap operation. (Scottish Aviation Ltd. Mandatory Service Bulletin No. B-121/61, Issue 2 dated April 17, 1975, and Beagle "PUP" Series Service Manual No. 121/02/3.68 pertain to this subject). This amendment becomes effective April 29, 1976.
2005-20-12: The FAA is superseding an existing airworthiness directive (AD) for Type R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12, and R334/4- 82-F/13 propeller assemblies. That AD currently requires initial and repetitive ultrasonic inspections of propeller hubs, part number (P/N) 660709201. This AD requires the same initial and repetitive ultrasonic inspections, but reduces the initial and repetitive compliance times for Type R334/4-82-F/13 propeller assemblies when used on Construcciones Aeronauticas, S.A. (CASA) 212 airplanes. This AD results from a report of a hub separation on a CASA 212 airplane. We are issuing this AD to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane. DATES: Effective October 28, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of October 28, 2005. The Director of the Federal Register previously approved the incorporation by reference of certain publications as listed in the regulations as of July 27, 2004 (69 FR 34560, June 22, 2004). We must receive any comments on this AD by December 12, 2005.
2017-17-17: We are superseding Airworthiness Directive (AD) 2011-03-08, which applied to certain Bombardier, Inc., Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. AD 2011-03-08 required an inspection to determine the number of flight cycles accumulated by certain accumulators installed on the airplane, and repetitive inspections of the accumulators for cracks, and replacement if necessary. This AD retains those inspections and the accumulator replacement if necessary, and adds a new terminating action to address the identified unsafe condition. This AD was prompted by the development of a terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
80-15-11: 80-15-11 KAWASAKI HEAVY INDUSTRIES, LTD.: Amendment 39-3853. Applies to Models KV107-II and KV107-IIA helicopters, certificated in all categories. Compliance required as indicated unless already accomplished. To prevent possible failure of aft transmission quill shafts, P/N 107D2067-1 and -3, accomplish the following: (a) Within 50 hours time in service after the effective date of this AD, remove from service all quill shafts, P/N 107D2067-1 and -3, that have accumulated 5990 hours or more time in service, and replace with a new part of the same part number. (b) Replace quill shafts, P/N 107D2067-1 and -3, that have less than 5990 hours time in service, with a new part of the same part number, when the parts have accumulated not more than 6040 hours time in service. This amendment becomes effective August 7, 1980.
2005-20-41: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -300 series airplanes, powered by Pratt & Whitney PW2000 series engines. This AD requires repetitive inspections for loose or damaged components of the support brackets and associated fasteners for the hydraulic lines located in the nacelle struts, and any related investigative and corrective actions. This AD results from reports of damage and subsequent failure of the support brackets and associated fasteners for the hydraulic lines located internal to the upper fairing cavity of the nacelle struts. We are issuing this AD to prevent such failure, which, in conjunction with sparking of electrical wires, failure of seals that would allow flammable fluids to migrate to compartments with ignition sources, or overheating of the pneumatic ducts beyond auto-ignition temperatures, could result in an uncontained fire.
98-13-10: This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) Model 182S airplanes. This AD requires repetitively inspecting all engine exhaust muffler end plates (four total) for cracks and replacing any muffler where an end plate is found cracked. The AD also requires fabricating and installing a placard that specifies immediately inspecting all engine exhaust muffler end plates any time the engine backfires upon start-up. This AD is the result of incidents where cracks were found in an engine exhaust muffler end plate on several of the affected airplanes. These cracks were caused by high stresses imposed on the attachment of the exhaust at the area of the firewall. The actions specified by this AD are intended to detect and correct damage to the engine exhaust mufflers caused by such high stress and cracking, which could result in exhaust gases entering the airplane cabin with consequent crew and passenger injury.
80-09-03 R1: 80-09-03 R1 BEECH: Amendment 39-3759 as amended by Amendment 39-3807. Applies to the following models and serial numbers of airplanes certificated in all categories having a Beech installed oxygen system: GROUP I MODEL SERIAL NUMBERS B90 LJ-490 thru LJ-501 C90 LJ-502 thru LJ-667 E90 LW-1 thru LW-326 H90 (Military T-44A) LL-1 thru LL-53 200 BB-2, BB-6 thru BB-185, BB- 187 thru BB-202, BB-204 thru BB-269, BB-271 thru BB-407, BB-409 thru BB- 468, BB-470 thru BB-482, BB-483 thru BB-488, BB-490 thru BB-509, BB-511 thru BB-518. 200T BT-1 thru BT-7 200C BL-1 and BL-2 A200 (Military C-12A) BC-1 thru BC-61 and BD-1 thru BD-30 A200 (Military C-12C) BC-62 thru BC-71 GROUP II MODEL SERIAL NUMBER C90 LJ-668 thru LJ-851 100 B-2 thru B-89 and B-93 A100 B-1, B-90 thru B-92, B-94, B- 100 thru B-247, except B-205 A100 (Military U-21F) B-95 thru B-99 B100 BE-1 thru BE-70 COMPLIANCE: Required as indicated, unless previously accomplished. To prevent seizure and binding of the oxygen control cable due to freezing of contaminating moisture which will interfere with actuation of the oxygen system, within the next 50 hours time-in-service after the effective date of this AD, accomplish the following: A) On airplanes listed in GROUP I of the applicability statement, locally fabricate, using letters at least 3/32" high, and install in clear view of the pilot, a placard which reads as follows: "Flight above 25,000 feet prohibited unless the oxygen system is ARMED (ON)." and operate the airplane in accordance with this limitation. B) On airplanes listed in Group II of the applicability statement, locally fabricate, using letters at least 3/32" high, and install in clear view of the pilot, a placard which reads as follows: "Flight above 25,000 feet prohibited unless the occupants are using oxygen" and operate the airplane in accordance with this limitation. C) Install a copy of theAD in the Limitation Section of the AFM of the airplanes listed in Group I and Group II of the applicability statement. D) The installation of the required placard and insertion of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person, who must make an entry in the airplane maintenance records indicating compliance with this AD. E) The placards specified herein may be removed from the airplane and a copy of the AD removed from the AFM upon modification of the airplane in accordance with Beechcraft Service Instructions No. 0867-341, Revision II, Part I, and recording of compliance with this paragraph in the airplane maintenance records. NOTE: The Beech Model H90 (Military T-44A), A100 (Military U-21F, S/N B-95 through B-99) and A200 (Military C-12A and C-12C) airplanes utilize P/N 90-384020-7, P/N 90- 384020-9 and P/N 90-384020-11, respectively, as replacement oxygen cable assemblies. These military airplanes and P/N 90-384020-11 cable assembly are not listed in Beechcraft Service Instruction No. 0867-341, Revision II. However, the replacement cable assemblies may be installed in these airplanes in accordance with said Service Instructions if removal of the placards is desired. F) Any equivalent method of compliance must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. Amendment 39-3759 became effective May 1, 1980. This Amendment 39-3807 becomes effective June 11, 1980.
78-23-13: 78-23-13 BRITISH AIRCRAFT CORPORATION: Amendment 39-3350. Applies to Viscount Model 744, 745D, and 810 Series airplanes, certificated in all categories. Compliance is required as indicated. The following parts are affected by this AD: 700 Series 800 Series 10" Oleos 14" Oleos Gland Nut 70050-317 72450-69 81050-69 Locking Plate 72450-71 81050-71 Locking Screw 70050-259 To ensure the security of the gland nut and locking plate/locking screw combination and prevent detachment of the gland nut of the main landing gear shock absorber struts, accomplish the following: (a) Within the next 25 landings after the effective date of this AD and thereafter at intervals not to exceed 25 landings from the last inspection until the inspection required by paragraph (c) of this AD is performed, visually inspect the gland nut and locking plate/locking screw combination as installed for security and satisfactory locking in accordance with paragraph 2.2 of the "Accomplishment Instructions" of British Aircraft Corporation Preliminary Technical Leaflet (PTL) No. 299 (700 Series) or PTL No. 168 (800 Series), as applicable, both at Revision 3, dated January 12, 1977, or an FAA-approved equivalent. (b) If, during any of the inspections required by paragraph (a) of this AD, the gland nut is found to be loose or not adequately locked, before further flight, remove the gland nut and inspect the thread form in accordance with paragraph (c) of this AD. (c) Within 500 landings after the effective date of this AD, unless already accomplished within the last 2,500 landings, and thereafter at intervals not to exceed 3,000 landings, remove the gland nut and inspect the condition of the threads in accordance with the criteria established in paragraph 2.2.2 of British Aircraft Corporation PTL No. 299 (700 Series) or PTL No. 168 (800 Series), as applicable, both at Revision 3, dated January 12, 1977, or an FAA- approved equivalent. (d)If, during any inspection performed in accordance with paragraph (c) of this AD, the thread form of the gland nut is found unacceptable under the criteria referenced in paragraph (c) of this AD, before further flight, replace the gland nut with a serviceable part of the same part number found acceptable under those criteria. (e) If, during any of the inspections required by this AD, a locking plate is found worn or fractured, before further flight, replace the locking plate with a serviceable part of the same part number. Replacement locking plates may be installed with the shock absorber strut intact by parting the plate as illustrated in Figure 1 of British Aircraft Corporation PTL No. 299 (700 Series) or PTL No. 168 (800 Series), as applicable, both at Revision 3, dated January 12, 1977, or an FAA-approved equivalent. This amendment becomes effective December 18, 1978.
61-14-05: 61-14-05 LOCKHEED: Amdt. 307 Part 507 Federal Register July 11, 1961. Applies to All Model 1049 Series Aircraft. Compliance required as indicated. As a result of numerous occurrences of loss of main landing gear doors, the following inspections and rework are required. (a) Within the next 30 hours' time in service after the effective date of this AD and every 30 hours' time in service thereafter, conduct a visual inspection for cracks or loose fasteners in the front main landing gear door assemblies paying special attention to the front ribs and front hinge fittings. If any defects are found, they must be repaired or replaced prior to further flight, except that a ferry flight may be authorized in accordance with CAR 1.76 to a base where the required replacement or modifications are to be made. (b) When doors incorporating the modifications outlined in Lockheed 1049 Service Bulletin No. 2935, or FAA approved equivalent, are installed, the special inspections described in (a) may be discontinued. (c) Upon request of the operator, an FAA maintenance inspector, subject to approval of the Chief, Engineering and Manufacturing Branch, FAA Western 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 increase for such operator. (Lockheed 1049 Service Bulletin No. 2935 pertains to this subject.) This directive effective July 17, 1961. Revised July 26, 1961.
2005-20-38: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron (Bell) model helicopters modified with Aeronautical Accessories, Inc. (AAI), Supplemental Type Certificate (STC) SH2820SO or that have the affected AAI Parts Manufacturer Approval (PMA) parts installed. This action requires inspecting a certain part-numbered reservoir assembly adapter (adapter) for the counter bore depth (dimension D). If the dimension D of the adapter exceeds .860 inch, before further flight, this AD requires replacing the reservoir assembly and adapter with airworthy parts. This amendment is prompted by a report of a rupture of an adapter during nitrogen charging because of inadequate wall thickness for the operating pressures. The actions specified in this AD are intended to prevent the rupture of an adapter, uncontrolled jetting of pressurized gas from the nitrogen bottle, and subsequent injury to occupants or damage to the helicopter.
2017-17-07: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) Trent XWB-75, Trent XWB-79, Trent XWB-79B, and Trent XWB-84 turbofan engines. This AD requires inspection of the intermediate-pressure (IP) turbine stage 2 locking plates. This AD was prompted by a report of several IP turbine stage 2 locking plates cracked during module assembly. We are issuing this AD to correct the unsafe condition on these products.