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2016-20-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by a determination that the compliance times for certain post-repair inspections and certain allowable damage limits (ADLs) must be reduced in order to address fatigue. This AD requires identifying any repairs and ADLs used to assess or control any structural damage on certain structural areas, and corrective action if necessary. We are issuing this AD to prevent fatigue damage on primary structure and structural repairs, which could result in reduced structural integrity of the airplane.
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2001-13-28: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A. (RR) Olympus 593 Mk. 610-14-28 turbofan engines. This action requires replacement of the low-oil pressure (LOP) switch. This amendment is prompted by a report of the failure of the low pressure (LP) and high pressure (HP) rotor thrust bearings due to oil starvation that was caused by the loss of the LOP switch function and resulted in a delayed engine shutdown. The actions specified in this AD are intended to prevent the failure of the LOP switch to indicate an LOP event, which could contribute to uncontained engine failure due to oil starvation in the thrust bearings.
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2016-19-14: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 and A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321 series airplanes. This AD was prompted by a report of cracks found during maintenance inspections on certain lugs of the 10VU rack side fittings in the cockpit. This AD requires repetitive inspections for cracking of the lugs on the 10VU rack side fittings, and repair of any cracking. We are issuing this AD to prevent reading difficulties of flight-critical information displayed to the flightcrew during a critical phase of flight, such as an approach or takeoff, which could result in loss of airplane control at an altitude insufficient for recovery.
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2001-13-25: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-200 and -300 series airplanes, that currently requires repetitive inspections to detect chafing or arcing damage to the cable/wire and fuel tube assemblies on the right-hand side of each engine, and replacement with new components, if necessary. That AD also provides for an optional terminating action for the repetitive inspections required by that AD. This amendment requires accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent chafing of the cable/wire bundles against the fuel line, which could result in arcing and a consequent fire or explosion. This action is intended to address the identified unsafe condition.
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2001-13-20: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that currently requires a detailed visual inspection to detect damage to the terminal lugs on the 12XC and 15XE contactors and the mounting lugs on the 15XE contactor; corrective actions, if necessary; and certain conditional repetitive inspections. This action adds requirements for installation of a new mounting bracket for the 15XE contactor, modification of the cable attachment adjacent to the contactor, and replacement of certain terminal lugs on the 15XE contactor by terminal lugs with a thicker contact area. 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 excessive vibrations generated by the mounting configuration of the 15XE contactor, which could cause breakage of the terminal and mounting lugs on the 15XE contactors in the 101VU panel in the avionics compartment, resulting in loss of electrical power from the standby generator.
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78-17-03: 78-17-03 BELL HELICOPTER TEXTRON (BHT): Amendment 39-3282 as amended by Amendment 39-3359 (Airworthiness Docket No. 78-ASW-37). Applies to Model 212 helicopters certificated in all categories equipped with main transmission spiral bevel gear, P/N 204-040-701-3.
Compliance is required as indicated.
To minimize the possibility of failure of the input spiral bevel gear, P/N 204-040-701-3, used in the main transmission of Bell Helicopter Textron (BHT) Model 212 helicopters, accomplish the following:
a. Within the next 25 hours time in service after the effective date of this Airworthiness Directive (AD):
1. For helicopters with rotor brakes, remove the rotor brake quill assembly, P/N 205-040-300-1, as prescribed by paragraph 1 of Part I of BHT Service Bulletin No. 212-78-8, dated July 28, 1978, or later FAA approved revision.
2. For helicopters without rotor brakes, remove the cover plate, P/N 204-040-174-1, from the left side of the transmission.
3. Utilizing the opening provided by step 1 or step 2, above, inspect all 62 teeth of the main spiral bevel gear, P/N 204-040-701-3, as prescribed by paragraph 2 of Part I of BHT Service Bulletin No. 212-78-8, dated July 28, 1978, or later FAA approved revision.
4. Remove and replace any gear that does not meet the inspection requirements set forth in step 3, above. Utilize instructions in the appropriate maintenance and overhaul manual for this procedure.
5. Install cover, P/N 204-040-174-1, over rotor brake quill port, reinstall panels and cowling, and perform the ground run utilizing procedures prescribed by paragraphs 4, 5, and 6 of Part I of BHT Service Bulletin No. 212-78-8, dated July 28, 1978, or later FAA approved revision.
6. Install adjacent to the limitation placard on the rotor brake handle in the crew compartment a decal or placard with the following words: ROTOR BRAKE INOPERATIVE. Letters are to be 1/8-inch minimum height printed or embossed on a contrasting background.
b. Within 25 hours time in service after accomplishment of the requirements of paragraph a. of this AD, and thereafter at intervals not to exceed 25 hours time in service, conduct the inspections and replacement, if appropriate, prescribed by Part II of BHT Service Bulletin No. 212-78-8, dated July 28, 1978, or later FAA approved revision.
BHT Service Bulletin No. 212-78-8 pertains to and provides for accomplishing the intent of this AD except that in addition, paragraph a, step 6, of this AD must also be accomplished. BHT Service Bulletin No. 212-78-12 also provides instructions and details pertinent to this AD.
Except as specifically provided otherwise by this AD, the manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part thereof pursuant to 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 Service Manager, Bell Helicopter Textron, Post Office Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106, and at the Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591.
Equivalent means of compliance with the requirements prescribed by this AD may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Post Office Box 1689, Fort Worth, Texas 76101.
Amendment 39-3282 became effective August 21, 1978.
This amendment 39-3359 becomes effective November 22, 1978.
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89-22-16: 89-22-16 GARRETT ENGINE DIVISION: Priority Letter AD issued on October 26, 1989.
Applicability: Garrett Turbofan Engine Models TFE731-2, -5, -5AR, and -5R, certificated in any category, installed on, but not limited to, the following aircraft: Lear Jet M31, CASA 101, Falcon 900, Falcon 20-5, and BAe 125-800.
Compliance: Required as indicated, unless already accomplished.
To prevent an uncommanded engine acceleration or deceleration, accomplish the following:
(a) Review the engine log book or maintenance records on the previously listed engine models to determine if DEEC Part Number 2118002-6, 2118002-8, 2118002-9, or 2118002-201 with one of the following serial numbers is installed. Spare DEEC's must also be checked for applicable part number and serial number.
DEEC SERIAL NUMBERS
PN 2118002-6
PN 2118002-9
PN 2118002-20
68-1094
108-1159
48-1049
78-1128
58-138
68-1095
108-1160
48-1059
78-1129
58-139
69-1096
108-1161
48-1060
78-1130
58-140
68-1097
108-1162
48-1061
78-1131
58-145
68-1106
108-1163
48-1063
78-1133
58-147
68-1108
108-1164
48-1071
78-1134
58-148
68-1109
108-1166
48-1072
78-1135
58-150
68-1110
108-1167
78-1113
78-1136
108-151
68-1111
108-1168
78-1114
78-1137
108-152
68-1112
108-1169
78-1115
78-1138
108-153
108-1152
108-1170
78-1116
78-1139
108-154
108-1154
108-1171
78-1117
78-1140
108-155
108-1155
108-1172
78-1118
78-1141
108-157
108-1156
108-1173
78-1119
78-1142
108-159
108-1157
108-1174
78-1120
78-1145
108-160
108-1158
78-1121
78-1146
108-162
78-1122
78-1147
108-164
PN 2118002-8
78-1123
78-1148
108-165
47-778
78-1124
78-1149
108-166
77-861
78-1125
78-1150
108-167
77-862
78-1126
78-1151
108-168
77-873
78-1127
108-169
108-170
108-172
(b) Remove from service, if necessary, suspect serial numbered DEEC's listed in paragraph (a) with less than 50engine hours time since new within the next 25 engine operating hours after receipt of this priority letter AD, and DEEC's with 50 or more engine hours time since new within the next 100 engine operating hours after receipt of this priority letter AD, and replace with a serviceable DEEC.
NOTE: Refer to Garrett Service Bulletin (SB) TFE731-76-3049, dated October 6, 1989, to determine previous accomplishment with this AD, and for removal, installation, repair, and re-identification information for these suspect DEEC's.
(c) Repair and re-identify, before further flight, in accordance with the Garrett SB TFE731-76-3049, dated October 6, 1989, suspect serial numbered DEEC's listed in paragraph (a) installed on a spare engine or located as a spare part.
(d) Revise the applicable FAA Approved Airplane Flight Manual (AFM) to provide interim emergency procedures to flight crews on airplanes affected by paragraphs (a) and (b), within 10 calendar days after receipt of this priority letter AD, by adding the following:
EMERGENCY PROCEDURES
In the event that uncommanded engine acceleration or deceleration is experienced:
(1) Place power lever for the affected engine in an intermediate position (slightly aft of cruise).
(2) Select computer OFF on affected engine (remove electrical power to DEEC).
(3) Re-adjust power lever as necessary.
(4) Continue with affected computer OFF for the remainder of the flight.
NOTE: It is also possible that the DEEC malfunction may affect the reserve power function on engines so equipped; therefore, it is important to conduct the normal reserve power pre-flight check prior to flights during which reserve power may be used.
(e) A copy of this AD inserted in the FAA Approved AFM may be considered an acceptable means of compliance with the required AFM revision.
(f) 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.
(g) 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 priority letter AD or adjustments to the compliance schedule specified in this priority letter AD may be approved by the Manager, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 3229 East Spring Street, Long Beach, California 90806-2425.
(h) Documents pertinent to this priority letter AD may be obtained, upon request, from Garrett General Aviation Services Division, Distribution Center, 2340 East University, Phoenix, Arizona 85037; telephone (602) 255-2548, or may be examined at the office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket No. 89-ANE-42.
Priority Letter AD 89-22-16, issued on October 26, 1989,becomes effective immediately upon receipt.
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91-24-13: 91-24-13 SIKORSKY AIRCRAFT: Amendment 39-8100. Docket No. 91-ASW-07.
Applicability: All Sikorsky Aircraft Model S-76A helicopters, certificated in any category, equipped with forward spar cap angles, part numbers (P/N's) 76201-05001-103 and 76201-05001-104, forward spar web, P/N 76201-05001-101, and forward spar web doubler, P/N 76201-05001-107, and not equipped with Modification Kit 76070-20086 installed in accordance with Sikorsky Alert Service Bulletin No. 76-55-12, dated June 6, 1986.
Compliance: Required as indicated, unless already accomplished.
To prevent failure of the helicopter vertical pylon forward spar cap, web, and web doubler, accomplish the following:
(a) For helicopters that have attained 100 or more hours' time in service, comply with paragraph (c) within the next 25 hours' time in service after the effective date of this AD unless already accomplished within the last 25 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection.
(b) For helicopters that have not attained 100 hours' time in service on the effective date of this AD, comply with paragraph (c) before attaining 125 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service.
(c) Inspect for cracks in the forward spar cap angles, spar web, and web doubler and in repairs and reinforcements in the area of the tail rotor shaft cutout in the pylon forward spar and areas adjacent to the fuselage shear deck as follows:
(1) Remove the tail rotor drive shaft fairings in the vicinity of the vertical pylon, exposing the shear deck and vertical pylon forward spar.
(2) Clean all accessible areas around the tail rotor drive shaft cutout area in the vertical pylon forward spar using a clean cloth dampened with solvent P-D-680, Type II, or FAA-approved equivalent.
(3) Using a light, visually inspect the forward side of the spar for cracks in all areas adjacentto the shear deck attachment to the forward spar web and the web doubler.
(4) Using a light and mirror, visually inspect the aft side of the spar for cracks. Inspect through the tail rotor drive shaft cutout.
(5) If cracks are found in the spar web or spar web doubler or in their repair or reinforcement parts, accomplish the following:
(i) For each part, if multiple cracks are found or if a single crack equal to or in excess of 2 1/2 inches in length is found, replace cracked parts prior to further flight with new parts of the same part number; or if not previously repaired or reinforced, incorporate a repair procedure contained in Sikorsky Overhaul and Repair Instructions (O&RI) 76200-014B, or later FAA-approved revisions, or an equivalent procedure approved as noted in paragraph (d) of this AD.
(ii) If a single crack is less than 2 1/2 inches in length, visually inspect the part for crack length prior to the first flight of each day, and--
(A) Within 25 hours' time in service after finding a crack, replace or repair the part in accordance with paragraph (c)(5)(i), except
(B) Replace or repair the affected part in accordance with paragraph (c)(5)(i) before further flight, whenever the crack length reaches 2 1/2 inches.
(6) If a crack is found in the spar cap angles, replace the cracked spar cap angles prior to further flight with a new spar cap angle of the same part number in accordance with Sikorsky Maintenance Manual SA 4047-76-2, or approved equivalent procedures as noted in paragraph (d) of this AD.
(7) Reinstall the tail rotor drive shaft fairings after the inspections and rework, as necessary, of paragraphs (c)(1) through (c)(6) are completed.
(d) Alternate inspections, repairs, modifications, or other means of compliance which provide an equivalent level of safety, may be used if approved by the Manager, Boston Aircraft Certification Office, FAA, New England Region, 12 New England Executive Park,Burlington, Massachusetts, 01803.
(e) On request of an operator, an FAA maintenance inspector, subject to prior approval of the Manager, Boston Aircraft Certification Office, may extend the repetitive inspection interval specified in this AD if the request contains justifying data.
(f) This amendment supersedes Amendment 39-4711 (48 FR 39052, August 29, 1983), AD 83-17-07, as amended by Amendment 39-5017 (50 FR 15099, April 17, 1985), AD 83-17-07 R1, and by Amendment 39-5332 (51 FR 24134, July 2, 1986), AD 83-17-07 R2.
(g) This amendment (39-8100, AD 91-24-13) becomes effective on December 20, 1991.
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2022-25-06: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-402 airplanes. This AD was prompted by an investigation that found that the actual operating temperatures within the integrated flight cabinet (IFC) were significantly higher than anticipated during certification. This AD requires a modification to improve the IFC cooling capacity. The FAA is issuing this AD to address the unsafe condition on these products.
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2016-20-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, and -400ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the skin lap splice is subject to widespread fatigue damage (WFD). This AD requires repetitive external detailed and surface high frequency eddy current (HFEC) inspections of the outer skin for cracking around fastener heads common to the inboard fastener row of the skin lap splice and corrective action. We are issuing this AD to detect and correct fatigue cracking of the skin lap splice, which could grow and result in possible rapid decompression and reduced structural integrity of the airplane.
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