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2011-14-07: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires removing the 15th stage HPC disk within 12,000 cycles since new (CSN) or, for any disks that exceed 12,000 CSN after the effective date of this AD using a drawdown plan that includes a borescope inspection (BSI) or eddy current inspection (ECI) of the rim for cracks. This AD was prompted by multiple shop findings of cracked 15th stage HPC disks. We are issuing this AD to prevent cracks from propagating into the disk bolt holes, which could result in a failure of the 15th stage HPC disk, uncontained engine failure, and damage to the airplane.
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66-20-02: 66-20-02 HAWKER SIDDELEY: Amdt. 39-273, Part 39, Federal Register August 13, 1966. Applies to de Havilland Model 104 Dove Series Airplanes Equipped With an Engine Fire Extinguisher System.
Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished.
(a) Inspect the engine air intake fire extinguishing system nozzle assembly to determine that 0.25 inch diameter radial holes are present in nozzle jet, P/N P.117. Replace each nozzle jet without 0.25 inch diameter radial holes with jet, P/N P.117e, with 0.25 inch diameter radial holes.
(b) Inspect the engine fire extinguishing system to determine that proper fire extinguisher bottle and flexible hoses from the fire extinguisher bottle to the firewall and from the firewall to the distributor are installed in accordance with Hawker Siddeley Aviation Ltd. Technical News Sheet CT (104) No. 196, Issue 1, or later ARB-approved issue or an FAA- approved equivalent. Replace improper fire extinguisher bottles and flexible hoses.
Hawker Siddeley Aviation Limited Technical News Sheet Dove (104) Series CT (104) No. 195, Issue 1, pertains to this subject.)
This directive effective August 13, 1966.
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2003-03-07: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires the installation of reinforcements in the lower portion of wing rib 15 on the left-hand and right-hand sides of the airplane. 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 reduced structural integrity of the wing flap support structure.
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97-14-05: This amendment supersedes Airworthiness Directive AD 95-20-06, which applies to certain Air Tractor Incorporated (Air Tractor) Models AT-301, AT-302, AT-400, AT-400A, AT-401, AT-402, AT-501, and AT-502 airplanes and currently requires repetitively inspecting the front spar attachment lugs and the rear spar for fatigue cracks, and modifying the vertical fin if cracks are found. The modification terminates the repetitive inspection requirement of AD 95-20-06 and may be incorporated at any time, if cracks are not found. The FAA has determined that the Air Tractor Models mentioned above with a 1/4-inch fin front spar fitting installed should be exempt from the AD. The AD will retain the requirements of AD 95-20-06 for all Air Tractor airplanes that have a 3/16-inch fin front spar fitting. The actions specified by this AD are intended to prevent in-flight vertical fin cracking, which, if not detected and corrected, could result in structural failure of the front spar attachments and eventually the rear spar attachment and cause loss of directional control of the airplane.
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2003-03-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777 series airplanes. This action requires revising the Airplane Flight Manual to specify that the engine anti-ice must be "on" during all ground and flight operations when icing conditions exist or are anticipated. This action is necessary to prevent ingestion of ice that could cause shutdown of both engines during operation in icing conditions, and result in a forced landing of the airplane.
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93-08-15: 93-08-15 AIRBUS INDUSTRIE: Amendment 39-8563. Docket 92-NM-215-AD.
Applicability: Model A320 series airplanes, manufacturer's serial numbers (MSN) 003 through 008, inclusive, and 010 through 021, inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent fatigue cracking, which may lead to reduced structural integrity of the main landing gear, accomplish the following:
(a) Prior to the accumulation of 12,000 landings, or within 500 landings after the effective date of this AD, whichever occurs later, modify the inner rear spar web in accordance with Airbus Industrie Service Bulletin A320-57-1004, Revision 1, dated September 24, 1992.
(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, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.
NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(d) The modification shall be done in accordance with Airbus Industrie Service Bulletin A320-57-1004, Revision 1, dated September 24, 1992, which includes the following list of effective pages:
Page Number
Revision Level
Shown on Page
Date
Shown on Page
1, 4, 12,
14-15, 17-18,
20
1
September 24, 1992
2-3, 5-11,
13, 16, 19,
21-30
Original
July 9, 1991
This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(e) This amendment becomes effective on June 11, 1993.
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2018-03-20: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-300 series airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a report indicating that a pipe of the fire extinguishing system in the forward cargo compartment was too long, and therefore could be installed only under stress, which applies pressure to the pipe clamp. We are issuing this AD to address the unsafe condition on these products.
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78-17-02 R3: 78-17-02 R3 PRATT & WHITNEY AIRCRAFT: Amendment 39-3281 as amended by Amendment 39-4334 and 39-4407 is further amended by Amendment 39-4818. Applies to Pratt & Whitney Aircraft models JT8D-9, - 9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines.
Compliance is required as indicated, unless already accomplished.
To detect cracks in compressor front hubs, P/Ns 594301, 791801, 640601, 743301, 750101, and 749801, except those excluded by serial number in Pratt & Whitney Aircraft Alert Service Bulletin No. 4841, Revision 6, dated July 15, 1983, which could result in fracture of the retention lugs and release of first stage fan blades, accomplish the following:
(A) Inspect front compressor front hubs for cracks in the blade slots in accordance with Pratt & Whitney Aircraft Alert Service Bulletin No. 4841, Revision 6, dated July 15, 1983, or equivalent means approved by the Manager, Engine Certification Branch, New England Region, and in accordance with limits specified in Paragraphs (B) and (C) of this AD. Remove cracked compressor front hubs prior to further flight.
(B) Hubs not previously inspected shall be inspected within 1,000 cycles from the effective date of this AD or before reaching the initial inspection limits specified in Column I of Paragraph (D), whichever occurs later, except do not exceed 13,000 total cycles. Repeat inspections at intervals listed in Column II, or Column III, Paragraph (D), thereafter.
(C) Hubs which have been previously inspected shall be reinspected within 1,000 cycles after the effective date of this AD or before reaching the initial inspection limit specified in Column I, Paragraph (D), or before reaching the repetitive inspection limits specified in Column II or Column III of Paragraph (D), whichever comes later. Repeat inspections at intervals listed in Column II or Column III, Paragraph (D), thereafter.
(D)
Model
Column I, initial inspection limit
(cycles)
Column II, Eddy
current repetitive
inspection limit
(cycles)
Column III, on-wing
ultrasonic repetitive
repetitive inspection
limit (cycles)
JT8D-9, -9A
13,000
6,000
2,000
JT8D-11
10,500
6,000
2,000
JT8D-15, -15A
9,500
5,000
1,500
JT8D-17, -17A
8,500
5,000
1,500
JT8D-17R, -17AR
8,000
5,000
1,500
NOTE: If the initial inspection or repetitive inspection is in paragraph (D) apply. If, however, the initial inspection or repetitive inspection is achieved by an eddy current inspection on an uninstalled engine, the Column II inspection limits of paragraph (D) would apply.
(E) Upon request of the operator, an FAA maintenance inspector, subject to the approval of the Manager, Engine Certification Branch, FAA, New England Region, may adjust the 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 that operator.
(F) For hubs that have been installed in more than one engine model, the inspection schedule for the engine model with the highest thrust rating in which it has operated is applicable.
The manufacturer's Alert Service Bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a). All persons affected by this directive who have not already received the service bulletin from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108. The service bulletin may also be examined at Federal Aviation Administration, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803.
Amendment 39-3281 became effective September 20, 1978.
Amendment 39-4334 became effective March 4, 1982.
Amendment 39-4407 became effective June 28, 1982.
This Amendment 39-4818 becomes effective March 30, 1984.
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66-18-04: 66-18-04 PIPER: Amdt. 39-266 Part 39 Federal Register July 26, 1966. Applies to Model PA-24-260 and PA-30 Airplanes, Serial Numbers 24-4247, 24-4300 through 24-4443, 24- 4445 through 24-4448, 24-4450 through 24-4452, 24-4454 through 24-4456, 24-4461, 24-4465, 24-4467, 24-4474, 24-4475, 30-853, 30-902 through 30-1087, 30-1089 through 30-1093, 30- 1095, 30-1096, 30-1098 through 30-1106, 30-1109, 30-1112, 30-1113, 30-1117, 30-1120, 30- 1127, and 30-1129 through 30-1137.
Compliance required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished.
To prevent inadvertent unlatching of the baggage door, accomplish the following:
(a) Inspect the baggage door latch to ensure that the latch extends through the latch striker plate 1/4 inch +0, -1/16 inch, measured from the top of the striker plate.
(b) If the latch does not extend 1/4 inch +0, -1/16 inch through the latch striker plate, before further flight accomplish the following, or an FAA-approved equivalent:
Replace the present latch striker plate retaining screws with AN 526-1032R14 screws and insert AN 960-10 washers between the door jamb and the latch striker plate, to obtain the 1/4 inch +0, -1/16 inch dimension. However, if more than three washers would be required, rework the door jamb to obtain the 1/4 inch +0, -1/16 inch dimension in an FAA-approved manner.
(Piper Service Letter No. 478, dated June 13, 1966, pertains to this subject).
This directive effective August 10, 1966.
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2003-02-05: This amendment adopts a new airworthiness directive (AD) for certain Eurocopter France (Eurocopter) model helicopters. This action requires measuring the diameter of the sliding door roller (roller) and the dimensions of the front end opening of the sliding door middle rail (rail) to determine if excessive wear exists, and if necessary, installing a placard prohibiting the operation of the sliding door during flight. This amendment is prompted by an incident in which a roller came out of the middle rail during a door-opening operation in flight. The actions specified in this AD are intended to prevent the roller from coming out of the middle rail when opening the door, which could lead to the sliding door separating from the helicopter during flight, damage to critical flight components, and subsequent loss of control of the helicopter.
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