The following are ADs applicable to commercial aircraft, engines and related components that are included in FAA Bi-weekly Report 2012-10 (May 21, 2012).
 
 
AIRBUS A330 and A340-200/-300 --- FAA AD 2012-09-13
Relates to EASA AD 2011-0032
This AD applies to Airbus Model A330-223F, -243F, -201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and -313 airplanes; certificated in any category; all manufacturer serial numbers, except airplanes on which Airbus modification 200616 has been embodied in production.
(g) Modification
At the later of the times specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable: Modify the NLG main fitting by adding primer paint to the cadmium around the dowel bush holes, in accordance with the Accomplishment Instructions of......
SB A330-32-3241 R01 (Airbus)
SB A340-32-4282 R01 (Airbus)
 
 
AIRBUS A300 --- FAA AD 2012-01-05
Supersedes FAA AD 2010-23-26
Relates to EASA AD 2011-0029
This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD; except airplanes on which Airbus Modification 11912 or 11932 has been installed.
(1) Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R airplanes.
(p) New Terminating Action
Within 30 months after the effective date of this AD: Modify the spot-faces around all the fastener holes at locations 43, 47 to 50, 52, and 54 (except for spot-faces of holes which have been previously repaired) on the bottom flange MLG ribs, in accordance with the Accomplishment Instructions of......
SB A300-57A0234 R05 (Airbus)
SB A300-57A0235 R05 (Airbus)
SB A300-57A0246 R04 (Airbus)
SB A300-57A0254 R01 (Airbus)
SB A300-57A6087 R05 (Airbus)
SB A300-57A6088 R04 (Airbus)
SB A300-57A6101 R04 (Airbus)
SB A300-57A6110 R01 (Airbus)
 
 
AIRBUS A319/A320/A321 --- FAA AD 2012-09-07
Relates to EASA AD 2011-0034
This AD applies to Airbus Model A319-111, -112, and -132 airplanes; Model A320-111, -211, - 212, -214 and -232 airplanes; and Model A321-111, -211, -212, and -231 airplanes; certificated in any category; having manufacturer serial numbers 0039, 0078, 0109, 0118, 0120, 0153, 0174, 0187, 0203, 0215, 0218, 0226, 0227, 0228, 0236, 0237, 0269, 0270, 0278, 0285, 0286, 0287, 0288, 0294, 0301, 0337, 0377, 0462, 0463, 0464, 0465, 0520, 0523, 0528, 0876, 0888, 0921, 0935, 0974, 1014, 1102, 1130, 1160, 1162, 1177, 1215, 1250, 1287, 1336, 1388, 1404, 1444, 1449, 1476, 1505, 1524, 1564, 1605, 1616, 1622, 1640, 1645, 1658, 1677, 1691, 1729, and 1905.
(g) Electrical Bonding Test and General Visual Inspection if Necessary
Within 24 months after the effective date of this AD, do an electrical bonding test to check for bonding between the re-fuel adaptor of the gravity fill and the top skin panels on the left-hand and right-hand wings, in accordance with the Accomplishment Instructions of......
SB A320-57-1152 (Airbus)
 
 
AIRBUS A319/A320/A321 --- FAA AD 2012-09-12
Supersedes FAA AD 2005-23-02
Relates to EASA AD 2010-0177
This AD applies to Airbus airplanes listed in paragraphs (c)(1), (c)(2), and (c)(3) of this AD; certificated in any category; all serial numbers; if equipped with one or more additional center tank(s) (ACT) with a part number (P/N) listed in table 1 of this AD. This AD does not apply to airplanes already having received Airbus modification 38036 in production. (1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (2) Model A320-211, -212, -214, -231, -232, and -233 airplanes. (3) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
(i) ACT Modification
Within 3,000 flight cycles or 24 months, whichever occurs first after the effective date of this AD: Modify the affected ACT listed in table 1 of this AD by replacing the manhole seal, in accordance with the Accomplishment Instructions of......
SB A320-28-1105 R02 (Airbus)
SB A320-28-1162 R02 (Airbus)
 
 
BOEING 767-200/-300/-400 --- FAA AD 2012-09-04
Supersedes FAA AD 2004-19-06R1
This AD applies to Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category; as identified in Boeing Service Bulletin 767-53A0100, Revision 3, dated February 6, 2012.
Note 1 to paragraph (c) of this AD: Supplemental Type Certificate (STC) ST01920SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a ''change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. For all other AMOC requests, the operator must request approval for an AMOC according to paragraph (o) of this AD.
(i) New Repetitive Detailed and Eddy Current Inspections
Prior to the accumulation of 15,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later: Perform detailed and eddy current inspections to detect cracking and/or corrosion of the fail-safe straps between the side fitting of the rear spar bulkhead at BS 955 and the skin, in accordance with......
SB 767-53A0100 (Boeing)
 
 
BOEING 767-200/-300 --- FAA AD 2012-09-08
This AD applies to The Boeing Company Model 767-200 and -300 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767-53A0139, dated November 12, 2009.
Note 1 to paragraph (c) of this AD: Supplemental Type Certificate (STC) ST01920SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a ''change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17.
(g) Repetitive Inspections
Except as provided by paragraph (h) of this AD: Before the accumulation of 43,000 total flight cycles, or within 1,600 flight cycles after the effective date of this AD, whichever occurs later, do detailed, low-frequency eddy current, and mid-frequency eddy current inspections for cracking of the aft pressure bulkhead at STA 1582, in accordance with the Accomplishment Instructions of......
SB 767-53A0139 (Boeing)
 
 
BOEING 737-700 --- FAA AD 2012-09-06
This AD applies to The Boeing Company Model 737-700 series airplanes, certificated in any category; as identified in the service bulletins specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD.
(1) Boeing Special Attention Service Bulletin 737-53-1286, Revision 1, dated December 14, 2009.
(2) Boeing Special Attention Service Bulletin 737-25-1598, dated December 8, 2009.
(3) Boeing Special Attention Service Bulletin 737-25-1599, dated January 20, 2010.
(g) Modifying Seat Track Structure
For airplanes identified in Boeing Special Attention Service Bulletin 737-53-1286, Revision 1, dated December 14, 2009: Within 72 months after the effective date of this AD, replace, with new components, certain floor panels, seat track pivot link assemblies, and seat track sections with new components, and modify certain seat tracks, in accordance with......
SB 737-25-1596 (Boeing)
SB 737-25-1598 (Boeing)
SB 737-25-1599 (Boeing)
SB 737-53-1286 R01 (Boeing)
 
 
BOEING 777 --- FAA AD 2012-09-14
This AD applies to The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 777- 52A0038, Revision 1, dated June 24, 2010
(g) Inspect Retention Bolt of Latch Pin Fittings No. 1 Through No. 8
At the applicable times specified in paragraph 1.E., "Compliance," of Boeing Alert Service Bulletin 777-52A0038, Revision 1, dated June 24, 2010, except as specified in paragraph (i) of this AD: Do a detailed inspection for fractured and/or missing latch pin retention bolts of the latch pin fittings of the lower sill of the forward large cargo door, and do all applicable related investigative and corrective actions, in accordance with......
SB 777-52A0038 R01 (Boeing)
 
 
FOKKER 100 --- FAA AD 2012-09-05
Relates to EASA AD 2009-0269R1
This AD applies to Fokker Services B.V. Model F.28 Mark 0100 airplanes, certificated in any category, all serial numbers, equipped with Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace Gloucester) main landing gear (MLG).
(g) Inspection for Part Numbers
Within 48 months after the effective date of this AD, do an inspection of the MLG to determine whether Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace Gloucester) MLG units having part number (P/N) 201072011, 201072012, 201072013, 201072014, 201072015, or 201072016 are installed on the airplane. A review of airplane maintenance records is......
SB SBF100-32-097 (Fokker)
SB SBF100-32-132 (Fokker)
SB SBF100-32-155 (Fokker)
SB SBF100-32-097 (Fokker)
SB F100-32-112 (Messier-Dowty)
 
 
PRATT & WHITNEY PT6A --- FAA AD 2012-09-10
This AD applies to Pratt & Whitney Canada PT6A-38, -41, -42, -42A, -61, -64, -66, -66B, -110, -112, -114, -114A, -121, -135, and -135A series turboprop engines:
(1) That have had maintenance done to the power section module involving first stage sun gear or planet gear replacement since December 22, 2008; and
(2) That have any of the following Timken Alcor Aerospace Technologies, Inc. (TAATI) part manufacturer approval (PMA) replacement first stage sun gears or planet gear sets installed:
(i) First stage sun gears P/N E3028456, all serial numbers (S/Ns).
(ii) First stage sun gears P/N E3037304, all S/Ns.
(iii) Planet gear sets P/N E3101455-02, all S/Ns.
(iv) Planet gear sets P/N E3101525-02, all S/Ns.
(f) Installation Prohibition
After the effective date of this AD, do not install on any airplane, any engine or power section module with a TAATI PMA replacement first stage sun gear or a planet gear set, as listed in paragraph (c) of this AD.
No Service Information documents referenced
 
 
ADM data is provided strictly and only for information and we do not guarantee its accuracy and currency.
 
 
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