DGAC-INDONESIA
List of Airworthiness Directives 2002
Sort by Type
No.
Number
Applicability
AEROSPATIALE ATR 42 SERIES
1 02-01-001
AEROSPATIALE, ATR 42-200, -300, and 320 models aircraft onwhich modification
8295 (SB. ATR42-53-0125) has not been
embodied.
PAGE - 1
27-Jun-2006
Reference
Subject
DGAC France AD 2001-554-087(B).
Wing to fuselage fairing panel (ATA 53).
2
02-01-002
AEROSPATIALE, ATR 42-200, -300, 320, -400 and -500 aircraft models on which
ATR mod. 5338 (SB.ATR42-32-0094) has
not been embodied.
DGAC France AD 2001-550-086(B).
Main Landing Gear - Swinging lever spacer.
3
02-01-003
AEROSPATIALE, ATR 42-200, -300, 320, -400 and -500 series airplanes equipped
with LABINAL engine fire handles P/Ns.
And S/Ns. As listed in the reference AD.
DGAC France AD 2001-281-078(B)R1.
Fire protection - Fire handles.
4
02-01-004
AEROSPATIALE, ATR 42-200, -300, 320, -400 and -500 series aircraft models on
which modification 5339 (SB. ATR42-270094) has not been embodied.
DGAC France AD 2001-387-085(B).
Flight controls - Normal pitch trim switches (ATA 27).
5
02-01-005
AEROSPATIALE, ATR 42-200, -300, 320, -400 and -500.
DGAC France AD 2001-449-082(B)R2.
Take-off after use of type II or IV fluids - Appendix to the
Flight Manual.
6
02-02-008
AEROSPATIALE, ATR 42-200, -300, -400,
and -500 series aircraft models on which
ATR mod. 5338 (SB. ATR42-32-0094) has
not been embodied.
DGAC France AD 2001-614-089(B).
MLG - Swinging lever spacer (ATA 32).
7
02-02-009
AEROSPATIALE, ATR 42-400, and -500
series aircraft models on which non of ATR
mod. 5117 or 5322 (SB. ATR42-25-0134)
has been embodied.
DGAC France AD 2001-636-088(B).
Thermal/acoustical insulation materials (ATA 25).
8
02-03-019
AEROSPATIALE, ATR 42-200, -300, and 320 model aircraft.
DGAC France AD 2002-071-091(B).
Engines - High pressure oil pump - Pressure Regulating
Valve (PRV)(ATA 79).
9
02-07-008
AEROSPATIALE, ATR 42-200; -300; and 320 model aircraft
DGAC France AD 2002-070-090(B)R1.
Propellers - Pitch change system component (ATA 61).
10
02-10-004
AEROSPATIALE, ATR-400, and -500
series aircraft models on which ATR mod.
5385 (SB. ATR 42-55-0009) has not been
embodied.
DGAC France AD 2002-431(B).
Flight control interference (ATA 27, 55).
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No.
Number
Applicability
Reference
Subject
11
02-10-021
AEROSPATIALE, ATR model 42-500
aircraft.
DGAC France AD 2002-506(B).
Vertical stabilizer - Fin tip upper closure rib (ATA 55).
12
02-11-018
AEROSPATIALE, ATR 42 aircraft models 200, -300, -320 equipped with mod as
insicated in reference AD.
DGAC France AD 2002-539(B).
Forward attendant seat (ATA 25).
AIRBUS A300, A310 SERIES
13 02-01-011
AIRBUS INDUSTRIE, A310 aircraft, all
certified models and all serial numbers on
which the modification Nos.11350 and
12310 (SB.A310-54-2033 Rev.1) have not
been embodied in production.
DGAC France AD 2001-555(B).
Wing - to - engine pylon interface.
14
02-02-001
AIRBUS INDUSTRIE, A300 and A310
series aircraft.
DGAC France AD 2001-265(B)R1.
Navigation - Pitot probes (ATA 34).
15
02-02-002
AIRBUS INDUSTRIE, A 300, A 310, and
A 300-600 aircraft all certified models,all
serial numbers.
DGAC France AD 2001-603(B).
Landing gear normal extension /retraction mode - Inspection
of landing gear selector valves (ATA 32).
16
02-02-003
AIRBUS INDUSTRIE, A310 and A330
aircraft.
DGAC France AD 2001-606(B).
PPG AEROSPACE windshield (ATA 56).
17
02-02-016
AIRBUS INDUSTRIE, A310 aircraft, all
certified models and all serial numbers,
except for aircraft on which Airbus Industrie
mod. No. 12277 has been embodied in
production or SB. A310-22-2052 in service.
DGAC France AD 2000-115-304(B)R4.
Loss of auto-trim function.
18
02-02-017
AIRBUS INDUSTRIE, A310 aircraft, all
certified models and all serial numbers,
except for aircraft on which Airbus Industrie
mod. No.12100 or 12291 has been
embodied in production or on which Airbus
Industrie SB. A310-34-2157 has been
embodied in service.
DGAC France AD 2001-467(B).
EFIS Symbol Generator Unit (SGU) - Introduction of a new
standard (ATA 34).
19
02-02-019
AIRBUS INDUSTRIE, A310 aircraft, all
models, equipped with post mod.4886
vertical stabilizer.
DGAC France AD 2001-560(B).
Vertical stabilizer and rudder attachment fittings (ATA 53,
55).
by ssi
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PAGE - 3
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No.
Number
Applicability
Reference
Subject
20
02-02-022
AIRBUS INDUSTRIE, A310 aircraft, all
certified models, all serial numbers, except
for aircraft on which Airbus Industrie mod.
No. 12277 has been embodied in production
or SB.A310-22-2052 in service.
DGAC France AD 2001-463(B).
Autoflight - Electrical pitch trim.
21
02-03-014
AIRBUS INDUSTRIE, A310 aircraft.
DGAC France AD 2000-481-324(B)R1.
Fuel Tanks - Electrical connections of fuel sensor (ATA 28).
22
02-03-020
AIRBUS INDUSTRIE, A300, A310 and
A300-600 aircraft, all certified models, all
serial numbers, equipped with Messier
Bugatti parking brake operated valves
(PBOV) P/N.A25315-1, with a serial
numbers between H2372 and H2989
inclusive.
DGAC France AD 2001-510(B).
Yellow hydraulic system - Parking brake operated valve
(PBOV)(ATA 32).
23
02-03-026
AIRBUS INDUSTRIE, A310 aircraft, all
certified models. The applicability of each
action rendered mandatory is defined in
paragraph 3 of this AD and shown in the
following summary as listed in the reference
AD.
DGAC France AD 2001-072(B)R2.
Throttle control - Inspection and modifications (ATA 76).
24
02-04-014
AIRBUS INDUSTRIE, A310 aircraft all
certified models and all serial numbers
except aircraft on which Airbus Industrie
mod. 11847 has been embodied in
production or SB. A310-28-2130 in service.
DGAC France AD 1998-174-248(B)R1.
Fuel tanks - Bonding Leads (ATA 28).
25
02-05-009
AIRBUS INDUSTRIE, A310, all certified
models and all serial numbers equipped with
Pratt & Whitney engines PW 4000 except
for aircraft on which mod. 12468 was
embodied in production or aircraft modified
in service according to SB. A310-79-2004
DGAC France AD 2002-173(B).
PW 4000 engine oil circuit flexible hose (TITEFLEX)(ATA
79).
26
02-05-018
AIRBUS INDUSTRIE, A300, A310, and
A300-600 aircraft, all certified models and
all serial numbers.
DGAC France AD 2002-185(B).
Transformer - Rectifier Units (TRU) - Temporary revision of
MMEL (ATA 24).
27
02-06-019
AIRBUS INDUSTRIE, A300,A310 and
A300-600 aircraft,all certified models,all
serial numbers, equipped with MESSIER
BUGATTI parking brake operated valves
(PBOV) PN A25315-1, with a serial number
between H2371 and H2989 inclusive.
DGAC France AD 2001-510(B) RI.
Yellow hydraulic system- Parking Brake Operated Valve
(PBOV).
by ssi
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List of Airworthiness Directives 2002
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PAGE - 4
27-Jun-2006
No.
Number
Applicability
Reference
Subject
28
02-06-021
Required as indicated in the reference AD.
DGAC France AD 2002-264(B).
THALES AVIONICS equipment failure of transformers
(ATA34).
29
02-07-012
AIRBUS INDUSTRIE, A310 and A300
aircraft, all certified models and all serial
numbers.
DGAC France AD 2002-264(B)R1.
THALES AVIONICS equipment failure of transformers
(ATA 34).
30
02-08-015
AIRBUS INDUSTRIE, A310 and A300-600
aircraft, all certified models except for
A300F4-605R and F4-622 models, all serial
numbers, on which Airbus serial mod.
No.06925 has been embodied.
DGAC France AD 1999-013-276(B)R1.
Fuselage - Frame FR73A at the level of the aft pax door
(ATA 53).
31
02-08-016
AIRBUS INDUSTRIE, A310 aircraft, all
certified models and all serial numbers, on
which Airbus mod. No.08888 and No.08889
have not embodied in production.
DGAC France AD 2000-514-326(B)R1.
Fuselage - Chafing plates of wing root (ATA 53).
32
02-08-017
AIRBUS INDUSTRIE, A310 all certified
models and all serial numbers which were
not inspected in accordance with Airbus
Industrie - SB. A310-57-2084 original issue
or any later approved revision.
DGAC France AD 2002-263(B).
Airbus A310 aircraft RAT (Ram Air Turbine) ejection jack
gimbals assembly (ATA 29, 57).
33
02-08-018
AIRBUS INDUSTRIE, A310 all certified
models and all serial numbers, except for
aircraft on which Airbus Industrie mod. No.
12248 has been embodied.
DGAC France AD 2002-170(B).
Inspection of the spacing between FQI probes and the
structure (ATA 28).
AIRBUS A330 SERIES
34 02-01-009
AIRBUS INDUSTRIE, A330 aircraft all
certified models, all serial numbers.
DGAC France AD 2001-191(B)R1.
Pax/Crew and emergency exit doors - Inspection of girt bar
attachment fittings.
35
02-01-010
AIRBUS INDUSTRIE, A330 aircraft,
models -341, -342, and -343, all serial
numbers fitted trimmable horizontal
stabilizer actuators (THSA) P/N.47172 or
47147-400.
DGAC France AD 2001-356(B)R1.
THSA - Inspection of ball-nut transfer tubes.
36
02-01-012
AIRBUS INDUSTRIE, A330 aircraft, all
certified models and all serial numbers.
DGAC France AD 2001-545(B).
Elevator servo - controls - life limits.
37
02-01-013
AIRBUS INDUSTRIE, A330 aircraft, all
certified models and all serial numbers.
DGAC France AD 2001-527(B).
THSA - Operational life limit.
by ssi
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PAGE - 5
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No.
Number
Applicability
Reference
Subject
38
02-01-015
AIRBUS INDUSTRIE, A330 aircraft,
models -341, -342, and -343 equipped with
Rolls-Royce Trent 700 engines.
DGAC France AD 2001-528(B).
Thrust reversers - C - Ducts.
39
02-01-015R1
AIRBUS INDUSTRIE, A330 aircraft,
models -243, -341, -342, and -343 equipped
with Rolls-Royce Trent 700 engines.
DGAC France AD 2001-528(B)R1
Thrust reversers - C - Ducts (Rolls-Royce Trent 700
engines)(ATA 78).
40
02-01-018
AIRBUS INDUSTRIE, A330 aircraft, all
certified models.
DGAC France AD 2001-530(B).
Aileron Servo - Controls - Life limits.
41
02-02-013
AIRBUS INDUSTRIE, A330-243, -341, 342, and -343 series aircraft, with RollsRoyce (RR) T700 engines.
DGAC France AD 2001-383(B)R1.
RR engine stall and shut down during acceleration from idle
(ATA 72).
42
02-02-018
AIRBUS INDUSTRIE, A330 aircraft
models, all manufacturer S/N. Fitted with at
least one spoiler servocontrol (SSC) with
part numbers as listed in the reference AD.
DGAC France AD 2001-609(B).
Spoiler - Uncommanded movement in flight (ATA 27).
43
02-02-021
AIRBUS INDUSTRIE, A330 aircraft
models as listed in the reference AD.
DGAC France AD 2001-465(B).
Escape-slides rafts - New rail release pins and new rail
adapters (ATA 25).
44
02-02-023
AIRBUS INDUSTRIE, A330 aircraft,
models -202, -223, -301, -321, -322, and 341 all serial numbers, lying between 0012
and 0223 inclusive, except as listed in the
reference AD.
DGAC France AD 1999-178-086(B)R1.
Slide/raft - Inspect slide and slide/raft release pin and
parachute pin installation (ATA 25).
45
02-02-024
AIRBUS INDUSTRIE, A330 aircraft,
certified in all models, all serial numbers.
DGAC France AD 2001-469(B).
Electrical and electronic installation - "Texas Instrument"
Circuit Breakers P/N. E0730-005 (ATA 92).
46
02-03-023
AIRBUS INDUSTRIE, A330 aircraft, all
certified models, all serial numbers.
DGAC France AD 2001-527(B)R1.
THSA - Operational life limit (ATA 27).
47
02-03-024
AIRBUS INDUSTRIE, A330 aircraft,
models -202, -223, -234, -301, -321, -322, 323, -341, -342 and -343, all serial numbers.
DGAC France AD 2001-465(B)R1.
Escape-slides/slide rafts - New rail release pins and new rail
adapters (ATA 25).
48
02-03-025
AIRBUS INDUSTRIE, A330 aircraft, all
certified models, all serial numbers.
DGAC France AD 2001-191(B)R2.
Pax/Crew and emergency exit doors - Inspection of girt bar
attachment fittings (ATA 52).
49
02-03-027
AIRBUS INDUSTRIE, A330 aircraft, all
serial numbers, fitted with Trimmable
Horizontal Stabilizer (THSA) P/N.47172.
DGAC France AD 2002-038(B).
Modification to THSA's P/N.47172(ATA 27).
by ssi
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PAGE - 6
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No.
Number
Applicability
Reference
Subject
50
02-03-031
AIRBUS INDUSTRIE, A330 aircraft,
models -202, -203, -223, -243, -301, -321, 322, -323, -341, -342 and -343, all serial
numbers.
DGAC France AD 2001-504(B)R1.
Nose landing gear - Inspection for corrosion under nose
wheel steering system - Rotating sleeve (ATA 32).
51
02-03-032
AIRBUS INDUSTRIE, A330 aircraft,
models -301, -321, -322, -341, and -342
which have not received either Airbus
Industrie mod.42418 (or Airbus Industrie
SB. A330-534-3013 at original issue or any
further approved revision).
DGAC France AD 2001-507(B).
Inspection of the lower flange and radius of floor beam
between FR47 and FR48 (ATA 53).
52
02-04-001
AIRBUS INDUSTRIE, A330 aircraft,
models -202, -223, -243, -301, -321, -322, 323, -341, -342 and -343 all serial numbers
fitted with trimmable horizontal stabilizer
actuators (THSA) P/N.47147-400.
DGAC France AD 2001-356(B)R2.
THSA - Inspection of ball-nut transfer tubes (ATA 27).
53
02-04-002
AIRBUS INDUSTRIE, A300 all certified
models, all serial numbers, equipped with
Messier-Bugatti Parking Brake Operated
Valve (PBOV) as listed in the reference AD.
DGAC France AD 2001-317(B)R1.
Blue hydraulic circuit - Parking Brake Operated Valve
(PBOV)(ATA 32).
54
02-04-003
AIRBUS INDUSTRIE, A330 as listed in the
reference AD.
DGAC France AD 2001-359(B)R1.
Emergency Door 3 Type I (LH & RH) - Escape slide
parachute pin (ATA 25).
55
02-04-012
AIRBUS INDUSTRIE, A330 aircraft,
models -202, -203, -223, -243, -301, -321, 322, -323, -341, -342 and -343 all serial
numbers.
DGAC France AD 2001-504(B)R2.
Nose landing gear - Inspection for corrosion under nose
wheel steering system - Rotating sleeve (ATA 32).
56
02-04-013
AIRBUS INDUSTRIE, A330 aircraft,
models -202, -223, -234, -301, -322, -323, 341, -342, and -343 all serial numbers
equipped with escape slide P/Ns. 7A1509101 through -117, S/Ns. AD001 through
AD0855, at the door 3 type I.
DGAC France AD 2001-359(B)R2.
Emergency door 3 type (LH & RH) - Escape slide parachute
pin (ATA 25).
57
02-04-015
AIRBUS INDUSTRIE, A330 aircraft.
DGAC France AD 2001-135(B).
"Incorrect Nav. Guidance upon F-PLN sequence" and" No
way point sequecing" (ATA 22).
58
02-06-020
AIRBUS INDUSTRIE, A330 aircraft,all
certified models and all serial numbers that
are In-service for more than six months at
the effective date of this AD.
DGAC France AD 2002-262(B).
Landing gear-Seizure of shortening mechanism (ATA32).
by ssi
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No.
Number
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Reference
Subject
59
02-07-009
AIRBUS INDUSTRIE, A330-243, -341, 342, and -343 series aircraft, with RollsRoyce (RR) T700 series engines.
DGAC France AD 2001-383(B)R2.
RR engine stall and shut down during acceleration from idle
(ATA 72).
60
02-07-011
AIRBUS INDUSTRIE, A330 aircraft, 202, -223, -243, -301, -321, -322, -323, 342, and -343 models, with the following
serial numbers : (See list AD).
DGAC France AD 2002-297(B).
Pax/Crew and emergency doors - Girt bar attachment fittings
(ATA 52).
61
02-09-005
AIRBUS INDUSTRIE, A330 aircraft,
models -202, -203, -223, -243, -301, -321, 322, -323, -341, and -343 all serial numbers.
DGAC France AD 2002-414(B).
THSA - Repetitive inspection and modification of ball-nut
transfer tubes, repetitive inspection and greasing of the
screw/nut assembly (ATA 27).
62
02-09-007
AIRBUS INDUSTRIE, A330 models -202, 223, -243, -301, -321, -322, -323, -341, -342
and -343 all serial numbers, which have
received Airbus mod. 45326 in production,
and which have received, in service, as listed
in the reference AD.
DGAC France AD 2002-368(B).
Inboard flap - Introduce new connection bolts on track 1
assembly (ATA 27, 57).
63
02-09-011
AIRBUS INDUSTRIE, A330 aircraft.
DGAC France T2002-459(B).
THALES AVIONICS DDRMI failure (ATA 34).
64
02-10-001
AIRBUS INDUSTRIE, A330 aircraft
models as listed in reference AD.
DGAC France AD 2002-434(B).
Wing - Outboard flap - Inspection of sensor strut at flap track
(ATA 27).
65
02-10-002
AIRBUS INDUSTRIE, A330 aircraft,
models -202, -203, -223, -243, -301, -321, 322, -323, -341, -342, and -343, all serial
numbers.
DGAC France AD 2002-422(B).
Ram Air Turbine - Inspection of position of rotary selenoids
(ATA 29).
66
02-10-003
AIRBUS INDUSTRIE, A330 aircraft
models as listed in reference AD.
DGAC France AD 2002-389(B)R1.
Spoiler - Uncommanded movement in flight (ATA 27).
67
02-10-008
AIRBUS INDUSTRIE, A330 aircraft,
models -202, -203, -223, -243, -301, -321, 322, -323, -341, -342, and -343 all serial
numbers.
DGAC France AD 2002-414(B)R1.
THSA - Repetitive inspection and modification of ball-nut
transfer tubes, repetitive inspection and greasing of the
screw/nut assembly (ATA 27).
68
02-11-008
AIRBUS INDUSTRIE, A330 aircraft, all
certified models, all serial numbers.
DGAC France AD 2001-527(B)R2.
THSA - Operational life limit (ATA 27).
69
02-11-009
AIRBUS INDUSTRIE, A330 series aircraft,
all certified models, all serial numbers.
DGAC France AD 2001-545(B)R1.
Elevator servo-control - Life limits (ATA 27).
by ssi
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PAGE - 8
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Reference
Subject
70
02-12-009
AIRBUS INDUSTRIE, A330 aircraft,
models -201, -202, -203, -223, -243, -301, 321, -322, -323, -341, -342, and -343, all
serial numbers.
DGAC France AD 2002-414(B)R2.
THSA - Repetitive inspection and modification of ball-nut
transfer tubes, repetitive inspection and greasing of the
screw/nut assembly (ATA 27).
71
02-12-010
AIRBUS INDUSTRIE, A330 aircraft,
models -201, -202, -203, -223, -243, -301, 321, -322, -323, -341, -342, and -343, all
serial numbers.
DGAC France AD 2001-504(B)R3.
Nose landing gear - Inspection for corrosion under nose
wheel steering system - Rotating sleeve (ATA 32).
BAE 125
72 02-02-028
BRITISH AEROSPACE, HS-125 series
airplanes; model Hawker 800 (U-125 up to
including serial number 258381), Hawker
800 XP (up to but not including serial
number 258490) certificated in any category.
FAA AD 2001-17-26.
To prevent of the cylinder head lugs, which could prevent the
main landing gear (MLG) from extending and result in a
partial gear-up landing.
BAe 146 and AVRO 146-RJ SERIES
73 02-02-015
BRITISH AEROSPACE, Bae 146 and Avro
146-RJ series aircraft, with mod.
HCM01037 embodied.
CAA AD 002-09-2001.
Fuselage - To inspect for possible fuselage skin chafing by
wing to fuselage fairing access panels (left and right side).
74
02-05-019
BRITISH AEROSPACE, Bae 146 and Avro
146-RJ series aircraft.
CAA AD 004-02-2002.
Air Conditioning - Environmental control system.
75
02-06-003
BRITISH AEROSPACE, Bae 146 and Avro
146-RJ seriea aircraft.
CAA AD 005-12-2001.
Flight Controls - To introduce elevator surface flight dampers
(left and right side).
BELL 407 SERIES
76 02-04-007
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 helicopters.
Transport Canada AD CF-1998-09R1.
Tail Rotor Gearbox.
77
02-05-011
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 helicopters.
Transport Canada AD CF-1998-09R1.
Tail Rotor Gearbox.
78
02-05-011
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 helicopters.
Transport Canada AD CF-1998-09R1.
Tail Rotor Gearbox.
79
02-05-012
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 helicopters.
Transport Canada AD CF-2002-18.
Tail Rotor Drive Shaft Bearings.
by ssi
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Reference
Subject
80
02-06-022
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 Helicopters,
S/N 53000 through 53475 with tailbooms
P/N 407-030-801-101,-105,-107 installed.
Transport Canada AD CF-1999-17R2
Tailboom Inspection and Modification.
81
02-10-029
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 helicopters,
serial number 53000 through 53442, with
flywheel, P/N. 407-040-316-101, installed,
certificated in any category.
FAA AD 2002-11-09.
To detect and crack in the forward bearing hanger bracket
(bracket) and to prevent loss of tail rotor drive or tail rotor
control and subsequent loss of control of the helicopter.
82
02-10-030
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 helicopters
serial number as listed in reference AD.
Transport Canada AD CF-2002-32R1
Bell 407 - Tailboom Tailrotor Gearbox Support Casting.
83
02-10-033
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 helicopter,
with serial numbers less than 53480,
certificated in any category.
FAA AD 2002-17-03.
To prevent a lack of electrical bonding that could result in an
electrical arc, ignition of fuel vapors, and an onboard fire.
84
02-11-010
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 helicopters,
serial numbers 53000 through 53538,
certificated in any category.
FAA Emergency AD 2002-23-51.
To detect an incorrect installation of swashplate drive link
cup washers (cup washer), which could limit the travel of the
swashplate outer ring and lead to stud failure, failure of both
swashplate drive link studs, and loss of control of the
helicopter.
85
02-12-003
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 407 helicopters.
Transport Canada AD CF-2002-18R1.
Tail Rotor Drive Shaft Bearings.
BELL 430 SERIES
86 02-04-006
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 430 helicopters.
87
02-10-015
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 430 helicopters,
S/Ns. 49001 through 49079, certificated in
any category.
BOEING 737 SERIES
88 02-01-021
BOEING, model 737-100, -200, -200C, 300, -400, and -500 series airplanes, line
numbers 1 through 3132 inclusive.
by ssi
Transport Canada AD CF-2000-32R2.
Electrical System Ground Faults.
FAA AD 2002-20-02.
To prevent accumulation of fuel in the right-hand upper fuel
enclosure area, a fire, and a subsequent forced landing.
FAA AD 2002-01-01
To prevent excessive in-flight vibration of the elevator tab,
which could lead to loss of the elevator tab and consequent
loss of controllability of the airplane.
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89
02-01-026
BOEING, model 737-100, -200, and -200C
series airplanes, as listed in Boeing Special
Attention SB.737-24-1144, Rev.1, dated
June 21, 2001; certificated in any category.
FAA AD 2001-24-33.
To prevent a short circuit and resultant arcing between the
power feeder wire bundle for the auxiliary power unit (APU)
generator and the first officer's elevator down control cable,
which could sever the control cable, and, if combined with a
subsequent failure of the captain's elevator down control
cable, result in loss of levator control of the airplane.
90
02-03-036
BOEING, model 737-200, -200C, -300,
and -500 series airplanes, as identified in
Boeing SB.737-57A1260, Rev.2, dated
October 18, 2001, vertificated in any
category.
FAA AD 2002-02-08.
To prevent the loosening and loss of the support pin retaining
bolt on the MLG, which could result in the loosening and
movement of the support pin, consequent cracked support
fitting, and collapse of the MLG.
91
02-04-016
BOEING, models 737-100, -200, -200C, 300, -400, -500 series airplanes; except
airplanes on which any replacement flap
tracks were installed according to Boeing
SB. 737-57-1203, dated November 15,
1999, or production equivalent.
FAA AD 2002-05-07
To find and fix discrepancies of the inboard tracks of the
outboards flaps, which could result in loss of the outboard
trailing edge flaps and consequent reduced controllability of
the airplane.
92
02-05-002
BOEING, model 737-200, -200C, -300, 400, and -500 series airplanes having line
numbers 292 through 2565 inclusive,
certificated in any category.
FAA AD 2002-07-08.
To find and fix cracking of certain fuselage lap joints, which
could result in sudden decompression of the airplane.
93
02-05-003
BOEING, model 737-200, -200C series
airplanes, having line numbers 1 through
291 inclusive, certificated in any category.
FAA AD 2002-07-11.
To find and fix cracking of certain fuselage lap joints areas,
which could result in rapid decompression of the airplane.
94
02-05-005
BOEING, model 737-200, -200C, -300, 400, and -500 series airplanes having line
numbers 292 through 2565 inclusive,
certificated in any category.
FAA AD 2002-07-10.
To find and fix prematur cracking of certain fuselage lap
joints repairs, which could result in rapid decompression of
the airplane.
95
02-06-012
BOEING, model 737-100,-200,-200C,-300,400 and-500 series airplanes: line numbers
(L/N) I through 3132 inclusive; certificated
in any category.
FAA AD 2002-10-11.
To detect and correct corrosion or cracking of the aft pressure
bulkhead at Body Station (BS) 1016, which could result in
loss of the aft pressure bulkhead web and consequent rapid
decompression of the fuselage.
96
02-06-013
BOEING, model 737-100,-200,-200C,-300,400 and-500 series airplanes; certificated in
any category.
FAA AD 2002-10-12
To prevent a disconnected aileron tab, which could lead to
severe airframe vibrations; consequent damage to the aileron
tab, aileron, and wing; and loss of controllability of the
airplane.
97
02-09-012
BOEING, all model 737-100, -200, -200C, 300, -400, -500, -600, -700, -800 and -900
series airplanes.
FAA AD 2002-19-51
To prevent operation with one failed flight control module
(FCM), which could result in reduced controllability of the
airplane, or with two failed FCMs, which could result in loss
of control of the airplane.
by ssi
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98
02-09-012R1
BOEING, all 737-100, -200, -200C, -300, 400, -500, -600, -700, -800 and -900 series
airplanes.
FAA Emergency AD 2002-19-51R1.
To prevent operation with one failed flight control module
(FCM), which could result in reduced controllability of the
airplane, or with two failed FCMs, which could result in loss
of control of the airplane.
99
02-10-009
BOEING, model 737-100, -200, -200C, 300, -400 and -500 series airplanes; line
numbers 1 through 3132 inclusive;
certificated in any category.
FAA AD 2002-18-02.
To prevent jamming of the first officer's control wheel due to
the presence of a foreign object on the lower bearing support
of the transfer mechanism for the aileron, which could result
in reduced controllability of the airplane.
100 02-11-002
BOEING, all 737 series airplanes,
certificated in any category.
FAA AD 2002-20-07.
To prevent an uncommanded ruddder hardover event and
consequent loss of control of the airplane due to inherent
failure modes, including single-jam modes, and certain latent
failure or jams combined with a second failure or jam.
101 02-11-017
BOEING, all model 737 series, model 747
series airplanes, and model 757 series
airplanes, certificated in any category.
FAA Emergency AD 2002-24-51.
To require the flightcrew to maintain minimum fuel levels in
the center fuel tanks, and to prohibit the use of the horizontal
stabilizer fuel tank (for model 747-400 series airplanes) and
certain center auxiliary fuel tanks (on model 747 series
airplanes).
102 02-12-011
BOEING, all model 737-100, -200, -200C, 300, -400, and -500 series airplanes;
certificated in any category.
FAA AD 2002-22-05.
To prevent severe flap asymmetry due to fractures of the
carriage spindles on an outboard mid-flap, which could result
in reduced control or loss of controllability of the airplane.
103 02-12-012
BOEING, all model 737 series airplanes,
certificated in any category.
FAA AD 2002-20-07R1.
To prevent an uncommanded rudder hardover event and
consequent loss of control of the airplane due to inherent
failure modes, including single-jam modes, and certain latent
failures or jams combined with a second failure or jam.
104 97-11-014R2
BOEING, model 737 series airplanes having
line numbers 1 through 2565 inclusive,
certificated in any category.
FAA AD 97-22-07.
To prevent sudden decompression of the airplane.
BOEING 747 SERIES
105 02-01-022
BOEING, model 747 series airplanes, as
listed in Boeing ASB.747-24A2118, Rev.3,
dated June 24, 1999.
FAA AD 2001-24-31.
To prevent chafing and burning of electrical wires, which
could result in smoke in the cockpit and loss of function of
several airplane system.
106 02-01-023
BOEING, model 747-100, -200, -300, and
747SR series airplanes powered by GE. CF645/50 series engines or Pratt & Whitney
JT9D-70 series engines.
FAA AD 2001-26-12.
To prevent heat damage to the diagonal brace, which could
cause cracking of fracture of the diagonal brace, and possible
loss of the diagonal brace load path and consequent
separation of the strut and engine from the airplane.
by ssi
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107 02-01-024
BOEING, model 747series airplanes, line
numbers 001 through 1207, certificated in
any category; excluding those airplanes
having line numbers 1174 and model 747 SP
series airplanes.
FAA AD 2001-23-13.
To prevent damage to the flap system, adjacent systems, or
structural components; or excessive skew of the trailing edge
flap; which could result in flap asymmetry and consequent
reduced controllability of the airplane.
108 02-01-025
BOEING, model 747 series airplanes, line
numbers 1 through 1046 and line numbers
1047 through 1271 inclusive; certificated in
any category.
FAA AD 2001-23-15.
To find and fix discrepancies of the installation of the
midspar fuse pins of the inboard and outboard strut, which
could result in loss of the secondary retention capability of
the fuse pins, migration of the fuse pins, and consequent loss
of the strut and engine from the airplane.
109 02-01-028
BOEING, model 747-100, -200B, -200C, 200F, 747SP, and 747SR series airplanes;
line numbers 001 through 310 inclusive;
certificated in any category.
FAA AD 2001-24-32.
To prevent chafing of certain electrical wire bundles located
behind the flight engineer's panel, which could result in
smoke in the cockpit, and uncommanded discharge of fire
extinguishing bottles for the No.4 engine and consequent
reduction of the ability to fight a fire in the No.4 engine.
110 02-02-005
BOEING, model 747 series airplanes; as
listed in Boeing ASB.747-35A2035, Rev.1,
dated July 22, 1999; certificated in any
category.
FAA AD 2001-24-29.
To prevent chafing between the oxygen hose and electrical
wire bundles at certain passenger service units, which could
result in arcing of a chafed wire bundle and consequent burnthrough of the oxygen hose, with the arcing potentially
representing an ignition source in an oxygen-enriched
environment.
111 02-02-027
BOEING, model 747-200 series airplanes,
as listed in Boeing ASB. 747-38A2073,
Rev.2, dated April 26, 2001, certificated in
any category.
FAA AD 2001-24-30.
To prevent water from dripping through certain floor panels
of the main deck cargo bay onto wire bundles and electronic
components, which could lead to the loss of function of
multiple electronic components and, consequently, could
reduce the flight crew's ability to operate in adverse
conditions.
112 02-03-034
BOEING, model 747-100, -200, -300,
747SP and 747SR series airplanes, powered
by P&W JT9D-3 or JT9D-7 series engines;
as listed in Boeing ASB. 747-54A2201,
dated September 28, 2000, certificated in
any category.
FAA AD 2002-05-01.
To prevent cracking of the vertical chords adjacent to the
lower spar fitting, which could result in separation of the
diagonal brace load path and lead to separation of the strut
and engine from the airplane.
113 02-04-017
BOEING, all model 747 series airplanes;
certificated in any category.
FAA AD 2002-06-02.
To find and fix cracking of the upper skin of the horizontal
stabilizer center section and the rear spar upper chord, which
could lead to reduced structural capability of the horizontal
stabilizer center section, and result in loss of controllability of
the airplane.
by ssi
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114 02-04-022
BOEING, model 747-100, -200, -300 and
747SR series airplanes; certificated in any
category; powered by General Electric (GE)
CF6-45/50 series engine, or Pratt & Whitney
JT9D-70 series engines.
FAA AD 2001-26-12.
To prevent heat damage to the diagonal brace, which could
cause cracking of fracture of the diagonal brace, and possible
loss of the diagonal brace load path and consequent
separation of the strut and engine from the airplane.
115 02-05-017
BOEING, model 747 series airplanes,
certificated in any category, line numbers 1
through 750 inclusive, excluding airplanes
on which the bulkhead splice areas have
been modified in accordance with Plan "B"
of AD 2001-11-06, Amdt. 39-12248.
FAA AD 2002-08-10.
To detect and correct cracked or broken alloy steel bolts on
the body station (BS) 1480 bulkhead splice and consequent
structural damage and rapid depressurization of the airplane.
116 02-06-011
BOEING, model 747 series airplanes,as
listed in Boing service Bulletin 74753A2349,dated october 12,2000;certificated
in any category.
FAA AD 2002-02-10.
To prevent loss of the structural integrity of the fuselage
which could result in rapid depressurization of the airplane.
117 02-09-001
BOEING, model 737-600, -700, -700C, 800, and -900; 747 and 757 series airplanes.
FAA Emergency AD 2002-18-52.
To prevent fuel vapors from coming into contact with an
ignition source in the center wing fuel tank, which could
result in fire/explosion in the center fuel tank.
118 02-10-027
BOEING, model 747-200B, -300, -400, 400D, and -400F series airplanes equipped
with General Electric (G.E) CF6-80C2
series engines, line number 679 through
1060 inclusive, certificated in any category.
FAA AD 2002-19-12.
To prevent blockage of the check tee valve and cracks in the
fire extinguisher discharge tubes in the engine struts,
preventing the fire extinguishing agent from being delivered
to the engine or reducing the amount delivered to the engine.
119 02-10-028
BOEING, model 737-600, -700, -700C, 800 and -900; 747 and 757 series airplanes,
certificated in any category.
FAA AD 2002-19-52.
To prevent fuel vapors from coming into contact with an
ignition source in the center wing fuel tank, horizontal
stabilizer fuel tank, center auxiliary fuel tank, or auxiliary fuel
tanks 1 and 4, which could result in fire/explosion.
120 02-11-016
BOEING, all 747-400, -400D, and -400F
series airplanes, certificated in any category.
FAA Emergency AD 2002-24-52.
To require the flightcrew to maintain minimum fuel levels in
the center fuel tanks, and to prohibit the use of the horizontal
stabilizer fuel tank.
CESSNA AIRCRAFT
121 02-01-006
CESSNA, model 172 series airplanes.
122 02-05-001
CESSNA, model U206 & TU206 series
airplanes.
by ssi
FAA AD 2001-23-03.
To detect and correct any chafing between the map light
switch and the bordering fuel line, which could result in a fuel
leak or an-flight fire.
FAA AD 2002-07-01.
To detect and replace structurally deficient horizontal
stabilizer attachment brackets.
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123 02-08-001
CESSNA, model 650 airplanes, serial
numbers -0001 through -0241 inclusive, and
serial numbers -7001 through -7112
inclusive; certificated in any category.
DC-10 AND MD-11 SERIES
124 02-02-004
McDONNELL DOUGLAS, DC-10-10, 10F, -10F, -15, -30, and -30F series
airplanes; as listed in Mc Donnell Douglas
ASB.DC10-24A174, dated June 29, 2001;
certificated in any category.
PAGE - 14
27-Jun-2006
Reference
Subject
FAA AD 2002-14-24.
To prevent inadvertent disengagement of the locking
mechanism of the side brace mechanism assembly of the left
or right main landing gear (MLG), which could lead to
collapse of the respective MLG, and result in gear-up landing
and possible injury to passengers and crew.
FAA AD 2001-24-23.
To prevent a loose ground stud and/or cable attachments, and
consequent chafing of adjacent structure and electrical arcing,
which could result in smoke/fire in the center accessory
compartment (CAC) in the event of fuel fuel leakage.
125 02-02-011
McDONNELL DOUGLAS, DC-10 series
airplanes, as listed in Boeing ASB.DC1024A149, Rev.2, dated April 05, 2001.
FAA AD 2001-24-21.
To prevent chafing of the wire bundle located behind the
flight engineer's panel caused by the wire bundle coming in
contact with the lower edge of the feed through and
consequent electrical arcing, which could result in smoke and
fire in the cockpit.
126 02-02-025
McDONNELL DOUGLAS, DC-10-30
series airplanes, as listed in Boeing ASB.
DC10-24A130, Rev.01, dated March 12,
2001; certificated in any category.
FAA AD 2001-24-20.
To prevent loss of protection by circuit breakers in the flight
engineer's equipment due to improperly wired connections at
the circuit breakers, which could result in wire damage and
could lead to smoke and/or fire in the cockpit.
127 02-02-026
McDONNELL DOUGLAS, DC-10-30
series airplanes, as listed in Boeing
ASB.DC10-24A137, Rev.01, dated May 31,
2001, certificated in any category.
FAA AD 2001-24-22.
To prevent loss of auxiliary power unit (APU) generator due
to chafing of the generator power feeder cable and
consequent electrical arcing and smoke/fire in the APU
compartment.
128 02-04-021
McDONNELL DOUGLAS, DC-10-10, 10F, -15, -30, -40 series airplanes,
certificated in any category; as identified in
Boeing ASB. DC10-24A170, Rev.01, dated
September 25, 2001.
FAA AD 2002-06-14.
To prevent wire chafing of the paralel power feeder cables of
the number 2 generator, which, if not corrected, could result
in electrical arcing and damage to adjacent structure, and
consequent smoke and/or fire in the aft door panel area.
129 02-06-009
Model DC-10-10, DC-10-10F, DC-10-15,
DC-10-30, DC-10-30F airplanes,
certificated in any category; except those on
which an additional locking system has been
installed on the thrust reverser on engine 1
and engine 3, according to paragraph (c) of
FAA AD 2
FAA AD 2002-08-17.
To prevent an uncommanded in-flight depployment of a
thrust reverser, which could result in reduced controllability
of the airplane.
by ssi
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130 02-08-004
McDONNELL DOUGLAS, DC-10-10, 10F, -15, -30, -30F, -40, -40F airplanes, and
model MD-10-10F and -30F, as listed in
Boeing ASB. DC10-28A228, including
Appendix, Rev. 01, dated July 16, 2001.
PAGE - 15
27-Jun-2006
Reference
Subject
FAA AD 2002-13-10.
To prevent arcing of connectors of the fuel boost/transfer
pump, which could result in a fire or explosion of the fuel
tank.
DE HAVILLAND DHC-7 SERIES
131 01-09-012R1
BOMBARDIER, DHC-7 aircraft.
DOT Canada AD CF-1999-03R1.
Bombardier Inc. DHC-7 - Baggage Door Stop Fitting.
132 02-01-014
BOMBARDIER, all model DHC-7 aircraft.
Transport Canada AD CF-98-03.
Corrosion Prevention and Control Program.
EUROCOPTER AS-332 SERIES
133 02-03-012
EUROCOPTER, AS 332 L2 helicopters
equipped with life raft assemblies, P/Ns.
00051047 and 00051048.
DGAC France AD 2001-500-019(A).
Life raft - Inflation cylinder (ATA 25).
134 02-06-023
EUROCOPTER, AS332 C,C1,L and L1
helicopter equipped with electrical multipurpose air intakes (MPAI) modified as
indicated of the reference AD.
DGAC France AD 2002-257-080(A).
Electrical multi - purpose air intakes (ATA30).
135 02-10-011
EUROCOPTER, AS 332 helicopters,
versions C, C1, L and L1, equipped with
main gearbox (MGB) main reduction gear
modules, P/Ns. 332A32-2027-00 and
332A32-2026-00, and equipped with bevel
gears, P/Ns. 332A-2181-00/-02/-03/-04, or
331A32-3110-07/-09/-19.
DGAC France Telegraphic AD T2002-424-081(A).
Crack in an MGB bevel gear.
136 02-10-018
EUROCOPTER, AS 332 helicopter versions
C, C1, L and L1 equipped with ferry tanks.
DGAC France AD 2002-508(A).
Ferry tanks attachments (ATA 53).
137 02-11-006
EUROCOPTER, AS 332 L2 helicopters
equipped with one or several main rotor
blades vibration absorbers P/N. 332A110460-02 that have logged more than 700
flight hours from new and are equipped with
a shaft as indicated in reference AD.
DGAC France Telegraphic AD T2002-573(A).
Main rotor blades vibration absorbers (ATA 62).
138 02-11-011
EUROCOPTER, AS 332 L2 helicopters
equipped with main rotor blade vibration
absorbers, part number 332A11-0460-02.
DGAC France Telegraphic AD T2002-582.
Main Rotor Blade Vibration Absorbers (ATA 62).
by ssi
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139 02-12-007
EUROCOPTER, AS 332 helicopters,
versions C, C1, L and L1 equipped with
MGB main reduction gear modules, part
numbers as listed in reference AD.
EUROCOPTER AS-350 SERIES
140 02-03-003
EUROCOPTER, AS 350 helicopters,
version B, BA, B1, B2, B3, BB and D,
equipped with tail rotor blades P/Ns. As
listed in the reference AD.
PAGE - 16
27-Jun-2006
Reference
Subject
DGAC France AD 2002-424-081(A)R1.
MGB - Bevel gear (ATA 63).
DGAC France AD 2001-640-089(A).
Tail rotor blades (ATA 05, 64).
141 02-03-010
EUROCOPTER, AS 350 B3 helicopters
equipped with Breeze 450-lb electric hoist
P/N. BL 29700-23.
DGAC France AD 2001-368-088(A).
Breeze 450-lb electric hoist (ATA 25).
142 02-03-015
EUROCOPTER, AS 350 helicopters,
versions B, BA, BB, B1, B2 and D equipped
with attachment screws
P/N.22201BC060008L (N510333728),
which ensure the tail boom-to-aircraft
structure junction attachment.
DGAC France AD 1997-147-072(A)R1.
Tail boom-to-aircraft structure junction attachment screws
(ATA 53).
143 02-04-008
EUROCOPTER, AS 350 version B, BA,
B1, B2, B3, BB and D helicopters equipped
with STARFLEX stars P/N.
350A31.1916.00.
DGAC France AD 2001-557-086(A)R2.
Main Rotor - Starflex star (ATA 05, 62).
144 02-05-014
EUROCOPTER, AS 350 version B3
helicopters before embodiment of Mod.
073146, serial numbers as indicated in the
reference AD.
DGAC France AD 2002-187-090(A).
Electrical power.
145 02-06-014
EUROCOPTER, AS 355 helicopters.
DGAC France AD 2001-558-064(A)R3.
Main rotor - Starflex star (ATYA 05, 62).
146 02-06-016
EUROCOPTER, AS 350 helicopters.
DGAC France AD 2000-340-080(A)R2.
Tail rotor drive shaft forward fairing (ATA 05, 53).
147 02-06-017
EUROCOPTER, AS 350 helicopters,
version B, BA, B1, B2, B3, BB and D fitted
with tail rotor hub pitch change plate P/Ns.
as indicated of the reference AD.
DGAC France AD 1999-085-076(A)R3.
Tail rotor hub pitch change plate bearing (ATA 05, 65).
148 02-06-018
EUROCOPTER, AS 355 Helicopters.
DGAC France AD 1999-084-057(A)R3.
Tail rotor hub pitch change plate bearing (ATA 05,65).
by ssi
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149 02-06-024
EUROCOPTER, AS 350 version
B,BA,B1,B2,B3,BB and D helicopters
equpped with STARFLEX stars P/N
350A31.1916.00, mounted on Main Rotor
Hubs (MRH) prior to the embodiment of
MOD 076221.
DGAC France AD 2001-557-086(A)R3.
Main Rotor - STARFLEX star (ATA05,62).
150 02-07-017
EUROCOPTER, AS 350 helicopters.
DGAC France AD 2002-344-093(A).
Sliding door - Wear on rollers and rails (ATA 05, 52).
151 02-07-018
EUROCOPTER, AS 355 helicopters.
DGAC France AD 2002-345-070(A).
Sliding door - wear on rollers and rails (ATA 05, 52).
152 02-08-009
EUROCOPTER, AS 350 helicopters,
versions B, BA, B1, B2, B3, BB and D
equipped with tail servocontrols all part
numbers that have not been modified per
Mod. 073139 or per Eurocopter AS 350 SB.
No. 67.00.22.
DGAC France AD 2001-580-085(A)R1.
Tail Servocontrol - Eye end fitting locking (ATA 67).
153 02-08-010
EUROCOPTER, AS 350 B3 helicopters
equipped with "TRW-SAMM" main
servocontrols P/N. as indicated in reference
AD.
DGAC France AD 2002-314-092(A).
"TRW-SAMM" Main Servocontrols (ATA 67).
154 02-08-011
EUROCOPTER, AS 350 helicopters
versions B, BA, B1, B2, B3, BB, and D
equipped with HIS KI 525A.
DGAC France AD 2002-281-091(A).
Navigation - Horizontal situation indicator KI 525A (ATA
34).
155 02-12-006
EUROCOPTER, AS 350 helicopters
versions B, B1, B2, B3, BA, BB and D,
delivered before July 1st 2002.
DGAC France AD 2002-537-094(A).
MGB - Mobile cowling seals.
EUROCOPTER AS-365 SERIES
156 02-03-011
EUROCOPTER, AS 365N helicopter
equipped with tail rotor pict change control
rods, P/N.365A33616121, component of a
"quiet" fenestron (post mod. 0764B39 or in
compliance with Eurocopter AS 365 SB.
No. 64.00.21).
157 02-03-018
EUROCOPTER, helicopters models as
listed in the reference AD, fitted with
SIREN cargo hooks P/N. AS-21-5-7.
by ssi
DGAC France AD 2001-443-054(A).
Tail Rotor head (ATA 65).
DGAC France AD 2002-044(A).
SIREN Carogo Hooks (ATA 05, 25).
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158 02-08-005
EUROCOPTER, AS 365 helicopters,
version N, N1, N2, and N3 equipped with
"TRW-SAMM" main servocontrols P/N, as
indicated in reference AD.
DGAC France AD 2002-312-056(A).
"TRW-SAMM" Main Servocontrols (ATA 67).
159 02-08-012
EUROCOPTER, AS 365 helicopters
versions N, N1, N2 and N3 fitted with MGB
P/N. 365 A 32.6000.00/02; 365 A
32.6001.00/01, modified per Mod 0763B79
(new O-ring seals) but not modified per
Mod.0763B76 (new reinforced attachment
studs).
DGAC France AD 2002-285-055(A).
MGB - Torque tightening of attachment studs (ATA 63).
160 02-10-017
EUROCOPTER, AS 365 helicopter version
N1, N2, and N3 equipped with tail rotor
blades P/N.365A12-0020-02.
DGAC France AD 2002-509(A).
A tail rotor blade failure which occurred in flight and caused
TGB/TRH assembly displacement and tail rotor drive shaft
disengagement.
EUROCOPTER SA-330 SERIES
161 02-01-016
EUROCOPTER, SA 330F, G, and J
helicopters.
DGAC France AD 2001-547-083(A); Eurocopter SA 330
ASB 65.104.
Main Gearbox - Oil cooler fan (ATA 65).
162 02-10-016
EUROCOPTER, SA 330 helicopter version
F, G, and J, equipped with ferry tanks.
DGAC France AD 2002-507(A).
Ferry tank attachment (ATA 53) - Hard landing during which
a ferry tank was torn off its attachments on the baggage
compartment floor.
163 02-10-031
EUROCOPTER, SA 330 F, G, and J; AS
332 C, C1, L, and L1; AS 350 B, BA, BB,
B1, B2, B3 and D; SA 365 C, C1, C2 and
C3; AS 365 N, N1, N2, and N3.
DGAC France AD 2002-452(A).
Main rotor and tail rotor dynamic components - Correction of
operating hours (ATA 62, 63, 64, 65).
FOKKER, F.28 SERIES
164 02-02-006
FOKKER, F.28 Mk.0100 aircraft; all serial
numbers, if equipped with Messier-Dowty
(formerly Dowty Rotol and Dowty
Aerospace Gloucester) MLG Units P/Ns. As
listed in the reference AD.
165 02-07-003
FOKKER, F.28 Mk.0070 and Mk.0100, all
serial numbers, if equipped with Dowty
Messier-Dowty MLG P/Ns. As listed in the
reference AD.
by ssi
BLA AD 2001-141.
Landing Gear - MLG main fitting - Inspection.
BLA AD 2002-060 (A).
Landing Gear - Main Landing Gear Sliding Member Inspection/Replacement.
DGAC-INDONESIA
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PAGE - 19
27-Jun-2006
Reference
Subject
166 02-07-004
FOKKER, F.28 Mk.0070, and Mk.0100
aircraft, all serial numbers; and Elevator
Tension Regulator Assemblies, including
units helds as spares, having P/Ns. D78179405, -407, -407, -411, -413.
BLA AD 2002-058(A).
Flight Controls - Elevator Tension Regulators Modification/Replacement.
167 02-07-005
FOKKER, F.28 Mk.0070 and Mk.0100
aircraft serial numbers as listed in Fokker
SB. F100-52-069, dated December 3, 2001.
BLA AD 2002-057(A).
Doors - Operating Button Status/Warning Lights - Installation.
168 02-07-010
FOKKER, F.28 Mk.0070 and Mk.0100, all
serial numbers.
BLA AD 2002-062.
Time Limits/Maintenance Checks - Maintenance
Requirements - Introduction.
169 02-09-004
FOKKER, F.28 Mk.0070 and F.28 Mk.0100
aircraft.
BLA AD 2002-111.
Equipment and furnishing - Pedestal side cover attachment Inspection/Modification.
170 02-09-010
FOKKER, F.28 Mk.0070 aircraft.
BLA AD 2002-112.
Electrical Power - Electrical Power Center Wiring.
171 02-10-005
FOKKER, F.28 Mk.0100 aircraft, all serial
numbers, if equipped with Messier-Dowty
(formerly Dowty Aerospace Gloucester)
MLG units.
BLA AD 2002-115.
Landing Gear - MLG Main Fitting - Inspection/Repair.
172 02-10-006
FOKKER, F.28 Mk.0100 aircraft, all serial
numbers, if equipped with Rolls-Royce
Tay650-15 engines.
BLA AD 2002-119.
Airplane Flight Manual - Engine Operating Limits &
Procedures - Amendments; Indicating/Recording - Flight
Warning Computer & Multi-Function Display Units Replacement; Engine - Fan Blades - Inspection(Upon
Exceedence of New Limits).
173 02-10-022
FOKKER, F.28 Mk.0070 and Mk.0100
aircraft, all serial numbers, if equipped with
Rolls-Royce Tay 650-15 engines in post-SB
TAY-73-1194 - configuration.
BLA AD 2002-121.
Engine - Low pressure fuel line - Inspection/Replacement.
GENERAL
174 02-02-012
B/E Aerospace (UK) Skyluxe II (AA2)
passenger seats, install on Airbus A320 and
A330 series aircraft.
175 02-03-001
GARMIN INTERNATIONAL, this AD
applies to the GNS 430 units that are
specified in paragraph (a)(1) of this AD and
are installed on aircraft. These GNS 430
units are installed as listed in the reference
AD.
by ssi
CAA AD 002-11-2001.
Hydrolok pin orientation.
FAA AD 2001-23-17.
To prevent external noise from causing inaccurate course
deviation displays in the GNS 430 unit's course deviation
indicator (CDI) or horizontal situation indicator (HIS). Such
displays could result in the pilot making flight decisions that
put the aircraft in unsafe flight conditions.
DGAC-INDONESIA
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27-Jun-2006
Reference
Subject
176 02-06-008
This AD applies to both passenger carrying
transport category airplanes and transport
category all-cargo airplane that have door
installed between the pilot compartment and
an occupid compartment.
CASR 121.313; CASR 121.587.
To prevent unauthorized access to the flightdecks of this
airplanes.
177 02-09-006
Required as indicated in the reference AD.
BLA AD 2002-103.
Rockwell Collins, Inc. Air Data Computer model ADC-85
and ADC-85A.
178 02-09-008
Hamilton Sundstrand Power System
(formerly Sunstrand Power Systems,
Turbomach, and Solar) models as indicated
in the reference AD.
FAA AD 2002-15-02.
To replace affected compressor wheels P/N. 100636-1, which
if not replaced, could result in uncontained compressor wheel
failure and damage to the airplane.
179 02-10-013
SICMA AERO SEAT, P/N as indicated in
the reference AD.
DGAC France AD 2002-471(AB).
Modification of seat belts attachment fittings (ATA 25).
180 02-10-019
SICMA AERO SEAT, types 90XX and
92XX passenger seats part numbers, as
defined in Annex 1 of Sicma Aero Seat SB.
92-25-005 last approved revision, all serial
numbers, right side only.
DGAC France AD 2002-504(AB).
Central spreaders modification (ATA 25).
181 02-10-020
SICMA AERO SEAT, passenger seats of
series 9801 and 9802, listed in Paragraph A
"Effectivity" of Sicma Aero Seat SB. 98-25014.
DGAC France AD 2002-505(AB).
In Flight Entertainment (IFE) electric harness protection in
central foldable armrest (ATA 25).
182 02-11-001
Britax Sell GmbH & Co. OHG water
boilers, coffee makers, and beverage
makers, listed by part number (P/N) and
serial number S/N) in table 1 of this AD.
FAA AD 2002-21-01.
To prevent a fire in the galley compartment due to inadequate
crimping of the electrical terminal contact pins, which could
result in smoke in the cockpit and cabin and loss of control of
the airplane.
183 02-11-004
AFD-3010 adaptive flight display units, part
number and serial number as listed in
reference AD, as specified in Rockwell
Collins SB. 12, Rev. 2, AFD-3010-31-12,
dated August 30, 2002.
FAA AD 2002-20-09.
To prevent premature failure of the Application Specific
Integrated Circuit (ASIC) device, which could result in the
AFD-3010 unit displaying erroneous primary flight and
engine parameter information. Such failure could lead to the
pilot using incorrect information when making critical flight
safety decisions.
184 02-12-002
Breeze Eastern Aerospace rescue hoist
series BL-16600, excluding BL-16600-160.
FAA AD 2002-20-05.
To prevent mounting bracket cracks, which could result in
mounting bracket failure and separation of the rescue hoist
from the helicopter.
IPTN CN235 SERIES
by ssi
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185 02-05-015
IPTN, CN 235 series airplanes (Indonesian
Aerospace (IPTN) Products).
186 02-10-025
CASA, model CN-235, S/Ns. C-006, C-007,
C-010, C-012, C-018, C-029, C-030, C-032,
C-033, C-042.
MD 900 SERIES
187 02-10-010
MD HELICOPTER, MD900 helicopters,
S/N. 900-00008, 900-00010 through 90000098, and 900-00100, with a lateral-mixer
bellcrank assembly (bellcrank), P/N.
900C2010203-105, installed, certificated in
any category.
PAGE - 21
27-Jun-2006
Reference
Subject
IPTN Mandatory SB N235-51-201, Rev. Original, issued 14
May 2002.
"CN 235 corrosion prevention and control program (CPCP)".
The corrosion problems in aircraft become more wide spread
and is more likely to occur concurrently with the other forms
of damage such as fatigue cracking. Corrosion degrades
structural integrity and if uncontrolled will reduce the
inherent ability to sustain fail safe loads in the presence of
other forms damage. This AD specifies inspection for
preventing and controlling safety related corrosion problems
in the CN 235 fleet.
DGAC Spain AD 02/02.
"Flight control - Rudder compensation control unit".
FAA AD 2002-15-07.
To prevent fatigue failure of the bellcrank and subsequent
loss of lateral control of the helicopter.
188 02-11-005
MD HELICOPTER, MD900 helicopters,
serial numbers 900-00008 through 90000110, with a main rotor support static mast
(mast), P/N. 900F2401021-101, certificated
in any category.
FAA AD 2002-22-51.
To detect cracks and pitting in the mast resulting in failure of
the mast, separation of the main rotor, and subsequent loss of
control of the helicopter.
189 02-11-013
MD HELICOPTER, MD900 helicopters,
S/Ns. 900-00008 through 900-00107, with
integrated instrument display system (IIDS),
P/N.900A3720002-107, -109, -111, or 113,
installed, certificated in any category.
FAA AD 2001-25-51.
To prevent failure of the IIDS and the subsequent inability to
monitor information and warning indications essential for the
operation of the helicopter.
190 02-11-014
MD HELICOPTER, MD-900 helicopters,
serial numbers 0008 through 0068,
certificated in any category.
FAA AD 2000-18-08.
To prevent damage to the longitudinal drive link, loss of
control of the main rotor system, and susequent loss of
control of the helicopter.
191 02-11-015
MD HELICOPTER, MD900 helicopters,
certificated in any category.
FAA AD 2000-10-06.
To prevent failure of the drive shaft due to fatigue, which
could result in total loss of drive to the main rotor hub and
subsequent loss of control of the helicopters.
OTHER AIRCRAFT
192 02-02-007
Fan Jet Falcon and Mystere Falcon 20-(X)5
aircraft.
by ssi
DGAC France AD 2001-600-028(B).
Aircraft structure - Windows frames (ATA 53).
DGAC-INDONESIA
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PAGE - 22
27-Jun-2006
Reference
Subject
193 02-02-010
Model G-IV series airplanes, S/Ns. 1253
through 1464 inclusive.
FAA AD 2001-26-07.
To prevent extinguishing agent from being discharged into
the wrong location, which could result in failure to extinguish
an in-flight fire on an affected engine and jeopardize
operation of the opposite engine.
194 02-02-014
PILATUS AIRCRAFT, PC-6 series
airplanes.
FOCA AD HB 2002-001.
Aileron mass balance weight and flettner tabs - Configuration.
Transport Canada AD CF-2001-40.
195 02-03-006
BOMBARDIER, DHC-8 aircraft models
Autopilot Servo Engagement.
102, 103, 106, 201, 202, 301, 311, 314, and 315, S/Ns. 003 through 580.
196 02-03-007
BOMBARDIER, DHC-8 aircraft as listed in
the reference AD.
Transport Canada AD CF-2001-42.
Inspection and replacement for fuselage to rear spar fittings.
197 02-03-008
BOMBARDIER, DHC-8 aircraft series 100,
200, and 300.
Transport Canada AD CF-2001-43.
De-Icing Boot Patch Limits.
198 02-03-013
BOMBARDIER, DHC-8 aircraft models
301, 311, 314, and 315 S/Ns. 100 through
583.
Transport Canada AD CF-2001-46.
Angle of Attack Sensor.
199 02-03-016
B-N Group BN2A series Islander and
BN2A-Mk.III Trislander series aircraft.
CAA AD 005-11-2001.
Nacelles/Pylons - Inspection of engine mounting brackets.
200 02-04-005
BOMBARDIER, DHC-8 model 311, serial
numbers 202 to 298.
Transport Canada AD CF-2002-08.
Bombardier DHC-8 - Bonding integrity inspection of
fuselage skin panels.
201 02-05-016
PILATUS AIRCRAFT, PC-6.
FOCA AD HB 2002-134.
To prevent the aircraft taking off with the horizontal stabilizer
incorrectly trimmed, which could result to loss of control, by
installing a trim warning system.
202 02-07-006
PILATUS AIRCRAFT, PC-6.
FOCA AD 2002-314.
To prevent the aircraft taking off with the horizontal stabilizer
incorrectly trimmed, which could result lead to control
difficulties as soon as the aircraft leaves the ground.
203 02-07-014
Short Brothers SD3-30 aircraft.
CAA AD 005-05-2002.
To prevent fire extinguishant blow back when discharging
through the existing fire extinguishing point adaptors.
204 02-07-015
PILATUS BRITTEN-NORMAN, Islander
and Trislander series aircraft.
CAA AD 004-05-2002.
To prevent the control column universal joint shouldered to a
smaller diameter than specified.
205 02-08-002
BOMBARDIER, DHC-8 aircraft, models
102, 103, 106, serial numbers 3 through
119, without modification 8/0864
incorporated.
Transport Canada AD CF-2002-29.
Bombardier DHC-8 - Aileron Tab Actuator Arms.
by ssi
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206 02-08-003
BOMBARDIER, DHC-8 aircraft, models
102, 103, 106, 201, 202, 301, 311, 314, and
315.
Transport Canada AD CF-2002-26.
Bombardier DHC-8 - Flap Drive Actuator Assembly.
207 02-11-003
Lake LA-4 model and serial number
airplanes as listed in paragraph (a)(1) of the
reference AD.
FAA AD 2002-21-05.
To prevent wing spar failure caused by cracks in the wing
spar doublers or angles, which could result in the wing
separating from the airplane with consequent loss of control.
208 02-11-012
PILATUS AIRCRAFT, model PC-6 series
airplanes, all manufacturers Serial Numbers
(MSN) up to and including MSN 939.
FOCA AD HB 2002-642.
Bellcrank assemblies - Bearing Housings Inspection/Replacement.
209 02-12-008
BOMBARDIER, Inc. DHC-6 series 1, 100,
and -200 aircraft with PreMod 6/1117 wings
that have accumulated less than 17,400
hours air time or 34,800 flight cycles.
Transport Canada AD CF-2002-40.
Wing Spar Strut Lug Inspection.
OTHER BOEING AIRCRAFT
210 02-01-027
BOEING, model 727-100 and -200; 737200, -200C, -300, -400, and -500; 747SR,
747SP series airplanes.
FAA AD 2001-24-02.
To prevent detachment of the shoulder restraint harness of the
attendant or observer seat from its mounting bracket during
service, which could result in injury to the occupant of the
seat.
211 02-03-035
BOEING, all model 727 series airplanes,
certificated in any category.
FAA AD 2002-04-06.
To find and fix cracking of the upper chord of the rear spar of
the wing, which could result in fuel leaking through the
cracks, reduced structural integrity of the wing, and
separation of the wing from the airplane.
212 02-05-004
BOEING, model 727 series airplanes, as
listed in Boeing SB. 727-53A0222, Rev.1,
including appendix A, dated March 15,
2001, certificated in any category.
FAA AD 2002-07-09.
To find and fix fatigue cracking in the lower skin panel at the
lower row of fasteners of the fuselage lap joints, which could
result in sudden fracture and failure of the lap joints, and
rapid decompression of the airplane.
213 02-07-013
BOEING, all model 727 series airplanes,
certificated in any category.
FAA AD 2002-12-13.
To prevent cracking of the elevator hinge support ribs, which
could lead to vibration of the airframe during flight and
consequent damage of the elevators and horizontal stabilizer,
potentially resulting in loss of controllability of the airplane.
214 02-09-014
BOEING, all model 727 series airplanes.
FAA AD 2002-17-05.
To find and fix discrepancies of the wire bundles and
hydraulic tubing in the aft stairwell area, which could result in
electrical arcing between the wiring and hydraulic tubing and
consequent fire and damage to adjacent structure.
OTHER BRITISH AEROSPACE AIRCRAFT
by ssi
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Number
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215 02-11-007
BRITISH AEROSPACE, HS 748 series
aircraft.
OTHER DOUGLASS AIRCRAFT
216 02-03-005
McDONNELL DOUGLAS, DC-9-81, -82, 83, and -87 series airplanes, and model MD88 airplanes, as listed in Boeing SB. MD8025-377, dated March 14, 2001, certificated
in any category.
PAGE - 24
27-Jun-2006
Reference
Subject
CAA AD 002-09-2002.
Fuel - Distribution - Chafe damage to a cross feed drain pipe.
FAA AD 2002-01-24.
To ensure replacement of dust seals of the lower passenger
service unit (PSU) panel that may contribute of the spread of
a fire when ignition occurs from electrical arcing of a failed
light holder assembly.
217 02-03-017
McDONNELL DOUGLAS, DC-9-82 series
airplanes, as listed in Boeing ASB. MD8027A359, Rev.01, dated March 26, 2001.
FAA AD 2002-03-06.
To prevent the flightcrew from performing a scheduled
landing on a runway of potentially insufficient length due to
failure of weight-on-wheels spoiler lockout mechanism
system and possible inactivation of the autospoiler actuator.
218 02-03-037
McDONNELL DOUGLAS, DC-9-10, -20, 30, -40, and -50 series airplanes, model DC9-81, -82, -83, -87 series airplanes, model
MD-88 airplanes as listed in McDonnell
Douglas SB.DC9-27-325R02, Rev.02, dated
December 12, 1995.
FAA AD 2001-24-27.
To prevent loss of rudder pedals control and reduction of
braking capability.
219 02-04-004
McDONNELL DOUGLAS, models and
series of airplanes as listed in the applicable
McDonnell Douglas SBs. Specified in table
of the reference AD, certificated in any
category.
FAA AD 2000-15-17R1.
To prevent hydraulic fluid leakage into the auxiliary power
unit (APU) inlet due to fatigue vibration and cracking in the
flared radius of a hydraulic pipe in the aft fuselage, which
could result in smoke and odors in the passenger cabin or
cockpit.
220 02-04-018
McDONNELL DOUGLAS, DC-9-10, -20, 30, -81, -82, -83 series airplanes, as listed in
McDonnell Douglas ASB. DC9-33A081,
Rev.01, dated November 8, 1999,
certificated in any category.
FAA AD 2002-24-17.
To prevent generation of smoke and fire in a cargo
compartment due to an illuminated light with a missing cover
contacting cargo contents for an extended period of time.
221 02-04-019
McDONNELL DOUGLAS, DC-9-81, -82, 83 and -87 series airplanes and MD-88
airplanes, as listed in McDonnell Douglas
ASB. MD80-24A126, Rev.02, dated
September 22, 1999, certificated in any
category.
FAA AD 2001-26-15.
To prevent smoke and fire in the flight deck and main cabin
due to insufficient clearance between wire assemblies and the
ice protection airduct and airstair door interlock rod, chafing
and consequent arcing of wire assemblies.
222 02-04-020
McDONNELL DOUGLAS, DC-9-81, -82, 83, and -87 series airplanes and MD-88
airplanes, as listed in Boeing ASB. MD8033A096, Rev.03, dated August 14, 2001;
certificated in any category.
FAA AD 2001-26-16.
To prevent electrical shorting and arcing due to the presence
of water in the lighting ballast interface connector, which
could result in smoke in the main cabin.
by ssi
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PAGE - 25
27-Jun-2006
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223 02-06-002
McDONNELL DOUGLAS, DC-9-81 (MD81), DC-9-82(MD-82),DC-9-83(MD-83),
DC-9-87(MD-87), and MD-88 airplanes, as
listed in Boeing SB. MD80-32-309, Rev. 01,
dated April 25, 2001, certificated in any
category.
FAA AD 2002-10-03.
To prevent fatigue cracking of the main landing gear (MLG)
shock strut pistons, which could result in any failure of the
MLG shock strut pistons, during landing or jacking of the
airplane, and consequent damage to the airplane structure and
injury to the passengers, flightcrew, or ground personnel.
224 02-06-004
McDONNELL DOUGLAS, DC-9-81(MD81), DC-9-82(MD-82),DC-9-83(MD-83),
and MD-88 airplanes, certificate in any
category, as listed in McDonnell Douglas
ASB. MD80-24A145, Rev. 01, dated June
22, 2000.
FAA AD 2002-09-06.
To prevent the alternating current (AC) power relay feeder
cable from chafing against the aft inboard side of electrical
power center, which could result in electrical arcing and
damage to adjacent structures, and consequent smoke and/or
fire in the electrical power center area.
225 02-06-005
McDONNELL DOUGLAS, DC-9-81(MD81), DC-9-82(MD-82),DC-9-83(MD-83),
and MD-88 airplanes, certificated in any
category, as listed in McDonnell Douglas
ASB. MD80-24A124, Rev. 01, dated
August 24, 2000.
FAA AD 2002-09-07.
To prevent possible arcing of the electrical power cables in
the aft compartment sidewall and consequent damage to
equipment and the adjacent structure, which could result in
smoke and/or fire in the cargo compartment.
OTHER HELICOPTER
226 02-03-009
EUROCOPTER, SA 315 B helicopters
equipped with MGBs P/Ns. 319A62-00-0001 to -4 having S/Ns. As listed in the
reference AD.
DGAC France AD 2001-368-045(A).
Main Gearbox - Pinion splines (ATA 05, 40).
227 02-04-011
BELL HELICOPTER TEXTRON
CANADA (BHTC), models 206L-4, 407
and 427 helicopters.
Transport Canada AD CF-2002-03R1.
K-Flex Drive Shaft.
228 02-05-010
BELL HELICOPTER TEXTRON
CANADA (BHTC), models 206L-4, 407
and 427 helicopters.
Transport Canada AD CF-2002-03R2.
K-Flex drive shaft.
229 02-05-013
BELL HELICOPTER TEXTRON INC.
(BHTI), model 204B, 205A, A-1, and B
helicopters.
FAA AD 2002-09-51.
To prevent failure of tail rotor grip and consequent loss of
control of the helicopter.
230 02-06-015
BELL HELICOPTER TEXTRON INC.
(BHTI), model 204B, 205A, A-1, and B
helicopters.
FAA AD 2002-09-51.
To prevent failure of the tail rotor (T/R) grip and subsequent
loss of control of the helicopter.
by ssi
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27-Jun-2006
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Subject
231 02-08-006
EUROCOPTER, AS 355 helicopters,
versions E, F, F1, F2 and N equipped with
tail servocontrols all part numbers that have
not been modified per Mod 073139 or per
Eurocopter AS 355 SB. No. 67.00.22.
DGAC France AD 2001-581-063(A)R1.
Tail Servocontrol - Eye end fitting locking (ATA 67).
232 02-08-007
EUROCOPTER, AS 355 helicopters,
versions F, F1, F2, and N equipped with
"TRW-SAMM" main servocontrols P/N. as
indicated in the reference AD.
DGAC France AD 2002-315-069(A).
"TRW-SAMM" Main Servocontrols (ATA 67).
233 02-08-008
EUROCOPTER, AS 355 helicopters
versions E, F, F1, F2, and N equipped with
HIS Kl 525A.
DGAC France AD 2002-280-068(A).
Navigation - Horizontal situation indicator Kl 525A (ATA
34).
234 02-08-014
EUROCOPTER, AS 355 helicopters,
versions E, F, F1, F2, and N equipped with
main gearbox (MGB) lubrication pumps, all
part numbers.
DGAC France AD 2002-331-071(A).
MGB - Lubrication PUMP (ATA 63).
235 02-10-012
SA 365 helicopter versions C, C1, C2 and
C3 fitted with MGB/P/N: 365 A
32.4000.02/03/05, modified per MOD
0763B79 (new-O-ring seals) but not
modified per MOD 0763B76 (new
reinforced attachment studs).
DGAC France AD 2002-283-048(A).
MGB - Torque tightening of attachment studs (ATA 63).
236 02-10-014
EC 155 helicopters, versions B, and B1,
equipped with ASU board 10 alpha 2, P/N.
SE07451, delivered before August 20, 2002.
DGAC France AD 2002-515(A).
Landing gear indicating system (ATA 31). - Landing gear not
extending in "NORMAL" and "EMERGENCY" extension
modes due to a short-circuit between two components of
ASU board 10 alpha 2.
237 02-10-026
BELL HELICOPTER TEXTRON INC.
(BHTI), model 212 helicopters, with a
vertical fin spar cap, part number a listed in
the reference AD.
FAA AD 2002-19-05
To prevent failure of a vertical fin spar, loss of a tail rotor,
and subsequent loss of control of the helicopter.
238 02-10-032
BELL HELICOPTER TEXTRON
CANADA (BHTC), models 206L-1, and
206L-3 equipped with IFR kit 206-705001, -101, -103 installed and all delivered
spare, magnetic brakes 204-001-376-003
manufactured byMemcor Truohm under part
number MP 498-3.
Transport Canada AD CF-2002-16.
Magnetic Brake.
by ssi
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239 02-12-005
BELL HELICOPTER TEXTRON
CANADA (BHTC), model 427 helicopters,
S/N. 56001 through 56034, 58001, and
58002.
RAYTHEON AIRCRAFT
240 02-01-007
RAYTHEON, models 58 series as listed in
the reference AD.
PAGE - 27
27-Jun-2006
Reference
Subject
Transport Canada AD CF-2002-45.
Cyclic Centering Switch Relocation.
FAA AD 2001-23-10.
To prevent separation of the flap flex shaft assembly caused
by improper heat treatment.
241 02-01-008
RAYTHEON, model 1900C and D series
aircraft.
FAA AD 2001-22-16.
To detect and correct cracked engine truss assemblies, which
could result in failure of the engine truss assembly and
consequent loss of airplane control.
242 02-03-004
RAYTHEON, this AD applies models and
serial numbers that are certificated in any
category and listed in the reference AD.
FAA AD 2002-01-10.
To detect and replace main landing gear torque knees, which
could result in failure of the main landing gear with
consequent loss of control of the airplane during takeoff,
landing, or other ground operations.
243 02-03-030
RAYTHEON, models as listed in the
reference AD.
CAA AD CF-1981-25R6.
Fatigue failure of the lower outboard forward wing panel
attachment fitting, and fatigue cracks in the lower forward
wing spar structure.
244 02-06-006
RAYTHEON, models 58P, 60, A60, B60,
65-88 aircraft.
FAA AD 2002-10-13.
To assure that clear and complete operating instructions are
visible for opening the exit doors, if not visible and
understandable, this could result in the inability to open the
exit door during and emergency situation.
245 02-07-002
RAYTHEON, model 58.
FAA AD 2002-11-07.
To prevent damage to the rotating beacon circuit breaker
switch or any other switch in the same location because of an
incorrect length electroluminescent panel retaining screw.
SIKORSKY S76 SERIES
246 02-08-013
SIKORSKY, S76A, B and C helicopters.
SOCATA TB 10 SERIES
247 02-03-002
SOCATA, this AD applies to TB aeroplanes
all models and all serial numbers, equipped
with the ammeter option.
248 02-06-007
SOCATA, TB9, TB10, TB200, TB20 and
TB21 aeroplanes.
by ssi
FAA Emergency AD 2002-15-51.
To prevent failure of a main rotor blade (blade) and
subsequent loss of control of the helicopter.
DGAC France AD 2001-446(A)R1.
To prevent incident in service due to problem in the ammeter
option.
DGAC France AD 2002-225(A).
To prevent a disconnecting of the aileron control gimbal joint
due to the failure of a shear pin which may lead to the loss of
aircraft roll control.