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CommutAir
S/N
554
FAA TC Hours Cycles Date Hours Cycles Date Hours Cycles Date
86-14-01 --
To prevent loss of
attitude/heading
reference information
14/07/1986
Amendment 39-5340. Applies to Sperry
Corporation AHZ-600 Attitude Heading
Reference System (AHRS), known to be
installed in, but not limited to,
DeHavilland Model DHC-8,
British Aerospace Model BAe 125-800,
Cessna Model 650, and Aerospatiale
Model ATR-42 series airplanes,
certificated in any category.
Modify the Sperry Corporation AH-600
Strapdown Attitude and Heading Reference Unit
(AHRU) by incorporating modifications in
accordance with the following Sperry Service
Bulletins or later revisions approved by the
Manager, Western Aircraft Certification Office,
FAA, Northwest Mountain Region:
21-1985-175, dated April 7, 1986
(Modification T);
21-1985-186, dated April 7, 1986
(Modifications S & V);
21-1985-187, dated April 7, 1986
(Modification U);
21-1986-19, dated April 22, 1986
(Modification Z);
21-1986-20, dated April 22, 1986
(Modification AA); and
21-1986-29, dated April 22, 1986
(Modification AB).
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A by Mod
87-06-02 --
To reduce the
possibility of AHRS
attitude and heading
computations being
contaminated, which
can result in frozen
attitude and heading
displays on both
instrument panels,
accomplish the
following
13/03/1987
Applicable to the following models of
Sperry Electronics Flight Instrument
Systems (EFIS) Symbol Generators,
which have not been modified to Mod
Level S or subsequent:
MODEL SPERRY PART NUMBER
SG-810 7004544-901
SG-811 7004544-811
SG-610 7004544-902
A. Prior to fiirther flight, install a placard
adjacent to the first pilot's electronic attitude
direction indicator (EADI), in full view of the pilot,
stating "FLIGHT INTO KNOWN IMC PROHIBITED."
B. Modification of the Sperry EFIS Symbol
Generator models listed above to Mod Level S or
subsequent, or installation of the following
Sperry EFIS Symbol Generator models,
constitutes terminating action of the operational
and placard requirements of paragraph A.,
above:
MODEL SPERRY PART NUMBERS MOD LEVEL (OR
SUBSEQUENT)
SG-811 7004544-211 V
SG-811 7004544-311 AD
SG-811 7004544-411 U
SG-611 7004544-611 S
B. Modification of the Sperry
EFIS Symbol Generator models
listed above to Mod Level S or
subsequent, or installation of the
following Sperry EFIS Symbol
Generator models, constitutes
terminating action of the
operational and placard
requirements of paragraph A.,
above:
MODEL SPERRY PART NUMBERS
MOD LEVEL (OR SUBSEQUENT)
SG-811 7004544-211 V
SG-811 7004544-311 AD
SG-811 7004544-411 U
SG-611 7004544-611 S
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A by Part Number
DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
1 of 11 11/8/2017
CommutAir
S/N
554
FAA TC Hours Cycles Date Hours Cycles Date Hours Cycles Date
DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
90-01-03 --Honeywell Attitude &
heading system05/02/1990
Honeywell AH-600 Attitude and Heading
Reference System (AHRS) Strapdown
Attitude and Heading Reference Unit
(AHRU), part numbers 7003360-931, -
932, -933, -934, -935, and -936, with
serial numbers 0100 through 0277.
Within 10 days after January 9, 1989 (the
effective date of Amendment 39-6093), inspect
airplanes with Honeywell AH-600 AHRS installed
to determine the part number, serial number,
and Mod Level of the strapdown AHRU installed
in the pilot’s (Number 1) AHRS. Prior to further
flight after inspection, remove all AHRU part
numbers 7003360-931, -932, -933, -934, -935,
and -936 with serial numbers 0100 through 0277,
without Mod Level ”F", from service in the pilot's
(Number 1) AHRS. Install the same part number
with Mod Level "F" incorporated, or modify the
AHRU in accordance with Honeywell Inc., Service
Bulletin 7003360-34-32, dated August 2, 1988.
Within 60 calendar days after the
effective date of this
amendment, inspect airplanes
with Honeywell AH-600 AHRS
installed to determine the part
number, serial number, and Mod
Level of the strapdown AHRU
installed in copilot's (Number 2)
AHRS and the auxiliary (Number
3) AHRS. Within 45 days after the
inspection, remove all AHRU part
numbers 7003360-931, -932, -
933, -934, -935, and -936, with
serial numbers 0100 through
0277, without Mod Level "F",
from service in the copilot's
(Number 2) AHRS and the
auxiliaiy (Number 3) AHRS. Install
the same part number with Mod
Level "F" incorporated, or modify
the AHRU in accordance with
Honeywell, Inc., Service Bulletin
7003360-34-32, dated August 2,
1988.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A by Part Number
90-06-13 --Honeywell vertical
gyro30/03/1990
Honeywell Model VG-14A vertical gyro,
part number 7000622-901, with serial
numbers listed in Honeywell Alert
Service Bulletin 21-1989-191, Revision 1,
dated November 20, 1989
Within 60 days after the effective date of this
AD, inspect the Model VG-14A vertical gyros to
determine the serial number.
1. If the vertical gyros have serial numbers listed
in Table 1 of Honeywell Alert Service Bulletin 21-
1989-191, Revision 1, dated November 20, 1989,
and have the letter "D" marked out on the
modification status plate, no further action is
required, and the airplane may be returned to
service.
2. If the vertical gyros have serial numbers listed
in Table 1 of Honeywell Alert Service Bulletin 21-
1989-191, Revision 1, dated November 20, 1989,
and do not have the letter "D" marked out on
the modification status plate, prior to further
flight, remove the gyro, replace the liquid levels,
test, and verify operation, in accordance with the
procedures specified in paragraph 2.,
Accomplishment Instructions, of the service
bulletin.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/AN/A , NO Vertical Gyro installed in
aircraft. AHRS and STBY Gyro only
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FAA TC Hours Cycles Date Hours Cycles Date Hours Cycles Date
DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
93-04-02 Rockwell transponders 26/03/1993
TDR-94D Mode S transponders, P/N CPN
622-9210-002, installed on, but not
limited to the following, certificated in
any category: Aerospatiale ATR-42 and
ATR-72 series airplanes Saab 340A and
340B airplanes Short Model SD3-60
airplanes de Havilland DHC-7 and DHC-8
series airplanes British Aerospace ATP
airplanes Gulfstream G-ll, G-lll, and G-IV
series airplanes Dassault Mystere-Falcon
50, Mystere-Falcon 200, and Mystere-
Falcon 900 airplanes Canadair Challenger
CL-601 airplanes British Aerospace HS
125-700A airplanes
Beechcraft 300 series airplanes
Within the next 10 calendar days after the
effective date of this AD, fabricate a placard with
the following words in letters at least 0.10-inch
in height and install this placard within the pilot's
clear view on the instrument panel: "OPERATION
OF TCAS II IN ANY MODE OTHER THAN THE "TA
ONLY" MODE IS PROHIBITED."
(b) Within the next 6 calendar months after the
effective date of this AD, modify the software of
the Mode S transponders in accordance with the
Accomplishment Instructions section of Collins
Service Bulletin TDR-94/94D-34-6, Revision 2,
dated September 21, 1992. The placard required
by paragraph (a) of this AD is no longer required
after this modification is incorporated.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A
N/A due to Part Number. Parts
Number 622-9210-007 installed on
aircraft.
94-01-06 -- Rockwell TCAS 04/02/1994
Traffic Alert and Collision Avoidance
System II processors that are installed
on, but not limited to the following
airplanes (all serial numbers),
certificated in any category: General
Aviation Airplanes: Astra Model 1125
airplanes; BAC Model 1-11 airplanes;
British Aerospace Model 125-800
airplanes; Beech Models C90A, B200,
300, 350, and 400A airplanes; Canadair
Models CL-600, CL-600-2B16, CL-601, CL-
601-1 A, and CL-601-3A airplanes;
Learjet Models 31, 55, and 60 airplanes;
Falcon Models 20, 50,200, and 900
airplanes Gulfstream Models G2 and G3
airplanes; British Aerospace Models HS-
125-700 airplanes; and Sabreliner Model
60 airplanes. Air Transport Airplanes:
Aerospatiale Models ATR-42 and ATR-72
airplanes; Airbus Industries Models
A300B2, A-300B, and A-320 airplanes;
British Aerospace Models ATP and 146
airplanes; Boeing Models 707, 727, 737,
747, 757, and 767 airplanes; British
Aerospace/Aerospatiale Model
Concorde SST airplanes; de Havilland
DHC-7 and DHC-8 series airplanes;
McDonnell Douglas Models DC-8, DC-9,
and DC-10, MD-80, and MD-11 airplanes;
Ilyushin Model IL-86 airplanes; Lockheed
Model L-1011 airplanes; SAAB Models
SF340A and SF340B airplanes; and Shorts
Models SD3-60-300 airplanes.
Prior to December 31, 1994, unless already
accomplished. To prevent collisions or near
misses caused by incompatibility between the
traffic alert and collision avoidance system
(TCAS) II processors and the current air traffic
control system, accomplish the following:
(a) Incorporate "Change 6.04A Enhanced" by
accomplishing either (1) or (2) below, as
applicable: (1) Remove any TCAS II processor
with a part number (P/N) suffix listed in the
"Existing P/N Suffix" column of the table below,
and install a corresponding TCAS II processor
with a P/N listed in the "New P/N Suffix" column
of the table below: Existing P/N Suffix New P/N
Suffix -001,-002,-011, -020 -012, or -612 -102,-
111, or-112 -120 -014 -320 NOTE 1: Collins SB No.
16, TTR-920-34-16, dated December 9, 1993,
specifies procedures for incorporating the
referenced New P/N suffixes.
(2) Change the part number of the TCAS II unit
on board the aircraft by reprogramming the
software with a data loader in order to obtain
the New P/N Suffix as specified in the following
table:
Existing P/N Suffix New P/N Suffix
-012 -020
-112 -120
-014 -320
NOTE 2: Units with P/N suffix of -001, -002, -011, -
102, -111, and -612 cannot be reprogrammed on
board the aircraft.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/AN/A by STC ST00844WI-D
installing TCAS II change 7.
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FAA TC Hours Cycles Date Hours Cycles Date Hours Cycles Date
DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
94-21-06 --Lap Belt Assemblies
and Restraint Systems11/25/1994
Lap belt assemblies and restraint
systems, as listed in Pacific Scientific SB
1108435-25-01, and Pacific Scientific SB
1108460-25-01; as installed on aircraft
and rotorcraft
Within 90 days after the effective date of this
AD, remove the applicable lap belt assemblies
and restraint systems, and replace them with
new design assemblies in accordance with Pacific
Scientific SB 1108435-25-01, or Pacific Scientific
SB 1108460-25-01, as applicable.
Pacific Scientific
SB 1108435-25-01
or
Pacific Scientific
SB 1108460-25-01
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/AN/A due Pacific Scientific not
installed on aircraft.
96-25-12 --Prevent compressor
wheel rupture13/01/1997
Sundstrand Aerospace SB No. SB-T-62T-
49-120, Revision 2, dated November 5,
1996 Sundstrand Aerospace SB No. SB-T-
62T-49-120, Revision 1, dated
September 9, 1996 Sundstrand
Aerospace SB No. SB-T-62T-49-120,
dated July 22, 1996
Remove from service compressor wheels in
accordance with the procedures described in the
Accomplishment Instructions of Sundstrand
Aerospace Service Bulletin (SB) No. SB-T-62T-49-
120, Revision 2, dated November 5, 1996,
Revision 1, dated September 9, 1996, or Original,
dated July 22, 1996, and the drawdown schedule
described in Table 2 of Revision 2 only, dated
November 5, 1996, and replace with serviceable
parts.
(b) This AD establishes a new life limit of 6,000
cycles for existing uninstalled compressor
wheels, identified as Sundstrand P/Ns 162690-1,
165111-1, and 167200-1.
Accomplishment Instructions of
Sundstrand Aerospace Service
Bulletin (SB) No. SB-T-62T-49-
120, Revision 2, dated November
5, 1996, Revision 1, dated
September 9, 1996, or Original,
dated July 22, 1996
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/AN/A due to Part Number of
Compressor Wheel
97-04-15 --Fire extinguisher
bottle cartridge07/03/1997
Fire extinguisher bottle cartridges
(squibs) having part numbers (P/N)
13083-10 and -25; as installed in, but not
limited to, the following airplane models,
certificated in any category:
de Havilland Model DHC-7 series
airplanes;
de Havilland Model DHC-8-100 and -300
series airplanes;
General Dynamics Convair Model 340,
440, and C-131 (military) series airplanes
modified in accordance with
Supplemental Type Certificate SA41100;
Lockheed Model 382 series airplanes;
and
Sabreliner Model NA-265-60, -65, and -
75A series airplanes.
Within 30 days after the effective date of this
AD, accomplish the following:
(1) Pull the applicable circuit breakers and
disconnect the electrical connector from any
Pacific Scientific Company, HTL/Kin-Tech
Division, fire extinguisher bottle cartridge (squib)
having P/N 13083-10 or 13083-25. CAUTION:
Prior to removing the electrical connector from
the fire extinguisher bottle cartridge, ensure that
the technician is grounded properly. Cartridges
are electrostatic discharge (ESD) sensitive.
(2) Perform a one-time visual inspection of the
electrical receptacle of the cartridge and its
mating connector to detect the presence of
aluminum foil in the area of the pins of the
cartridge and the connector. The aluminum foil
may have the appearance of solder. Remove any
aluminum foil that is present.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/AComplied with Ex Factory by
Tyrolean records.
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FAA TC Hours Cycles Date Hours Cycles Date Hours Cycles Date
DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
2001-15-
17--
Prevent such
erroneous altitude
interpretations
20/08/2001
This AD applies to CTL-92 transponder
control panel part numbers 622-6523-
204, 622-6523- 205, 622-6523-206, 622-
6523- 207, and 622-6523-208 (serial
numbers as specified in Rockwell Collins
Service Bulletin 33 (CTL-92-34-33), dated
April 2001), that are installed in aircraft.
These CTL-92 transponder control panels
are installed in, but not limited to, the
following aircraft that are certificated in
any category:
(1) Aerospatiale ATR42 and ATR72 series
airplanes;
(2) Saab Aircraft Models 340B and
SF340A airplanes;
(3) Embraer EMB-120 series airplanes;
(4) deHavilland DHC-8 series airplanes;
and
(5) Raytheon Models C90A, B200, 350,
and 1900D airplanes.
(1) Modify the altitude encoder inputs of the CTL-
92 transponder control panels. Within the next
10 hours time-in- service (TIS) after August 20,
2001 (the effective date of this AD). Modify in
accordance with the Accomplishment
Instructions section of Rockwell Collins Service
Bulletin 33 (CTL-92-34-33), dated April5, 2001.
(2) Do not install, on any aircraft, an affected CTL-
92 transponder control panel that has not been
modified as required by paragraph (d)(1) of this
AD. As of August 20, 2001 (the effective date of
this AD). Modify in accordance with the
Accomplishment Instructions section of Rockwell
Collins Service Bulletin 33 (CTL-92-34-33), dated
April5, 2001.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A
Part Number 622-6523-205
installed. S/N 12781 is N/A by S/B
CTL-92-34-33
2002-06-
06--
Prevent erroneous
altitude resolutions03/05/2002
This AD applies to TDR-94 Mode S
transponders (Collins part number (CPN)
622-9352-004) and TDR-94D Mode S
transponders (CPN 622-9210- 004) that
derive altitude information from a
Gillham (gray code) encoded pressure
altitude source and are installed on, but
not limited to, the following airplanes
that are certificated in any category: (1)
Aerospatiale ATR42 series airplanes; (2)
deHavilland DHC-7 and DHC-8 series
airplanes; and (3) Short Brothers Models
SD3-60 and SD3-60 SHERPA airplanes.
Determine whether the altitude information
from any TDR-94 Mode S transponder (CPN 622-
9352-004) or TDR-94D Mode S transponder (CPN
622-9120-004) is derived from a digital air data
source or a Gillham (gray code) encoded source.
Accomplish the modification in
accordance with Rockwell Collins
Service Bulletin No. 17 (TDR-
94/94D- 34-17), dated February
8,1999, Service Bulletin 17,
Revision No. 1, dated May 15,
2000, or Service Bulletin 20 (TDR-
94/94D-34-20), Revision No. 1,
dated May 2, 2001. Collins
Product Information Letter No.
71, dated January 1999,
references Service Bulletin 17,
dated February 8,1999.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/AN/A by Part Number. Part Number
622-9210-007
2009-21-
03
To prevent over-
fueling of the APU
during the start
sequence
11/20/09Hamilton Sundstrand Power Systems T-
62T-46C12 auxiliary power units (APUs)
At the next FADEC removal, but no later than 18
months after the effective date of this AD,
upgrade the software in the APU FADEC from
software version 02.01.000 to version 03.00.000,
and change the FADEC part number (P/N) from
4503069E to 4503069F.
(g) Use paragraphs 3. A through 3.F.(2) of the
Accomplishment Instructions of Hamilton
Sundstrand Power Systems Service Bulletin No.
4503067-49-12, Revision 2, dated March 9,2009,
to do the software upgrade and the FADEC P/N
change
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A
N/A by Model Number. APU
APS500/T-62-T-40C7B/167301-
101A installed on aircraft
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DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
2011-01-
09--
Protective Breathing
Equipment (PBE)9/2/11
B/E Aerospace protective breathing
equipment (PBE) units having part
number (P/N) 119003-11. These PBE
units may be installed on (or carried or
stowed on board), various transport
category airplanes, certificated in any
category.
Within 120 days after the effective date of this
AD, inspect to determine the serial number of
the PBE units installed in the aircraft, in
accordance with the Accomplishment
Instructions of B/E Aerospace Service Bulletin
119003-35-5.
(1) For any PBE that has a serial number from
003-50730M to 003-51329M inclusive: Before
further flight, replace the PBE with a serviceable
PBE, except as provided by paragraph (g)(2) of
this AD.
(2) For any PBE that has a label showing that it
has been restored in accordance with B/E
Aerospace Service Bulletin 119003-35-6: The
replacement has been done, and no further
action is required by paragraph (g) of this AD.
(3) For any PBE not having a serial number from
003-50730M to 003-51329M inclusive: No
further action is required by paragraph (g) of this
AD.
B/E Aerospace Service Bulletin
119003-35-6N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A
B/E Aerospace PBE not installed in
Aircraft. ESSEX PB&R
CORPORATION PBE Installed. Part
Number MR10049N.
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DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
2011-21-
08--
Sicma Aero Seat 88xx,
89xx, 90xx, 91xx, 92xx,
93xx, 95xx, and 96xx
series passenger seat
assemblies
11/23/11
This AD applies to Sicma Aero Seat 88xx,
89xx, 90xx, 91xx, 92xx, 93xx, 95xx, and
96xx series passenger seat assemblies
identified in Annex 1, Issue 2, dated
March 19, 2004, of Sicma Aero
Seat Service Bulletin 90-25-013, Issue 4,
dated March 19, 2004, that have
backrest links having part numbers
(P/Ns) 90-000200-104-1 and 90-000200-
104-2; and that are installed on, but not
limited to,
the airplanes identified in table 1 of this
AD, certificated in any category. This AD
does not apply to Sicma Aero Seat series
9140, 9166, 9173, 9174, 9184, 9188,
9196, 91B7, 91B8, 91C0, 91C2, 91C4,
91C5, 9301, and 9501 passenger seat
assemblies.
(f) Unless already done, do the following actions.
(1) At the later of the compliance times specified
in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, do a
general visual inspection of the backrest links
having P/Ns 90-000200-104-1 and 90-000200-
104-2, in accordance with Part One of Sicma
Aero Seat Service Bulletin 90-25-013, Issue 4,
dated March 19, 2004, including Annex 1, Issue
2, dated March 19, 2004:
(i) Before 6,000 flight hours on the backrest link
since new.
(ii) Within 900 flight hours or 5 months after the
effective date of this AD, whichever occurs
later.
(2) If, during the inspection required by
paragraph (f)(1) of this AD, cracking is found
between the side of the backrest link and the
lock-out pin hole but the cracking does not pass
this lock-out pin hole (refer to Figure 2 of Sicma
Aero Seat Service Bulletin 90-25-013, Issue 4,
dated March 19,2004, including Annex 1, Issue 2,
dated March 19, 2004): Within 600 flight hours
or 3 months after doing the inspection,
whichever occurs first, replace both backrest
links of the affected seat with new, improved
backrest links having P/Ns 90-100200-104-1 and
90-100200-104-2, in accordance with Part Two of
Sicma Aero Seat Service Bulletin 90-25-013, Issue
4, dated March 19, 2004, including Annex 1,
Issue 2, dated March 19, 2004.
(3) If, during the inspection required by
paragraph (f)(1) of this AD, cracking is found that
passes beyond the lock-out pin hole (refer to
Figure 2 of Sicma Aero Seat Service Bulletin 90-
25-013, Issue 4, dated March 19, 2004, including
Sicma Aero Seat Service
Bulletin 90-25-013, Issue 4,
dated March 19, 2004
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/AN/A DUE TO EQUIPMENT NOT
INSTALLED
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CommutAir
S/N
554
FAA TC Hours Cycles Date Hours Cycles Date Hours Cycles Date
DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
2011-23-
06--
Air Transport
Association (ATA) of
America Code 25:
Equipment/Furnishing
s.
11/21/11
(c) This AD applies to Sicma Aero Seat
Model 9401, 9402, 9404, 9505, 9406,
9407, 9408, and 9409 series passenger
seat assemblies, all part numbers,
except front row and aft facing seats,
and those modified to ''Amendment B''
standard. These passenger seat
assemblies are installed on, but not
limited to, ATR-GIE Avions de Transport
Régional Model ATR42-200, -300, -320,
and -500 airplanes and Model ATR72-
101, -201, -102, -202, -211, -212, and -
212A airplanes. Note 1: This AD applies
to Sicma Aero Seat passenger seat
assemblies as installed on any airplane,
(g) Within 6 months after the effective date of
this AD, perform a detailed inspection for
cracking of the central and lateral spreaders of
the affected seats, in accordance with paragraph
2/A1., ''Checking procedures of lateral and
central spreaders,'' of the Accomplishment
Instructions of Sicma Aero Seat Service Bulletin
94-25-013, Issue 4, dated February 12, 2008.
(1) If no cracking is found on any central
spreader, repeat the detailed inspection
thereafter at intervals not to exceed 550 flight
hours until the replacement specified in
paragraph (h) of this AD is done.
(2) If no cracking or only cracks that are shorter
than 8 millimeters (mm) (0.315 inch) are found
on any lateral spreader, repeat the detailed
inspection thereafter at intervals not to exceed
550 flight hours until the replacement specified
in paragraph (h) of this AD is done.
(3) If all cracks found on any central spreader are
shorter than 8 mm (0.315 inch), before further
flight, repair the affected spreader, in
accordance with paragraphs 2/A through C2. of
the Accomplishment Instructions of Sicma Aero
Seat Service Bulletin 94-25-011, Revision 3, dated
June 30, 2008. Within 550 flight hours after doing
the repair, do the detailed inspection specified in
paragraph (g) of this AD, and repeat the
inspection thereafter at intervals not to exceed
550 flight hours until the replacement specified
in paragraph (h) of this AD is done.
(4) If one or more cracks are found that are 8
mm (0.315 inch) or longer on any lateral or
central spreader, before further flight, replace
the affected spreader, in accordance with
Sicma Aero Seat Service Bulletin
94-25-012, Revision 1, dated
June 26, 2008.
S/S N/A N/A N/A N/A N/A N/A N/A N/A N/AN/A by P/N installed. This AD is
superseded by AD 2012-08-07
######## --
Joint Aircraft System
Component (JASC)/Air
Transport Association
(ATA) of America Code
3/13/12
This AD applies to Aviation
Communication & Surveillance Systems
(ACSS) traffic alert and collision
avoidance system (TCAS) units with part
numbers identified in ACSS Technical
Newsletter 8008359, Revision B, dated
August 3, 2011, as installed on but not
limited to various transport and small
airplanes, certificated in any category.
Note 1 to paragraph (c) of this AD: Table
1 of this AD also provides a cross-
referenced list of part numbers with
associated service bulletins to help
operators identify affected parts.
Within 36 months after the effective date of this
AD, upgrade software for the ACSS TCAS, in
accordance with the Accomplishment
Instructions of the applicable ACSS publication
identified in table 1 of this AD.
Note 2 to paragraph (g) of this AD: ACSS Service
Bulletin 8008233-001 (ATA Service Bulletin
9000000-34-6016), Revision 03, dated June 30,
2011, contains three part numbers (P/Ns
9000000- 10007, -20007, and -55007) that were
never produced.
Within 36 months after the
effective date of this AD,
upgrade software for the ACSS
TCAS, in accordance with the
Accomplishment Instructions of
the applicable ACSS publication
identified in
table 1 of this AD.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A by P/N installed
8 of 11 11/8/2017
CommutAir
S/N
554
FAA TC Hours Cycles Date Hours Cycles Date Hours Cycles Date
DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
######## --
Air Transport
Association (ATA) of
America Code 25:
Equipment/Furnishing
s.
5/9/12
(1) This AD applies to Sicma Aero Seat
Model 9401, 9402, 9404, 9405, 9406,
9407, 9408, and 9409 series passenger
seat assemblies, all part numbers,
except front row and aft facing seats,
and those modified to ''Amendment B''
standard. These passenger seat
assemblies are installed on, but not
limited to, ATR–GIE Avions de Transport
Régional Model ATR42-200, -300, -320,
and -500 airplanes and Model ATR72-
101, -201, -102, -202, -211, -212, and -
212A airplanes.
(2) This AD applies to Sicma Aero Seat
passenger seat assemblies as installed
on any airplane,
This paragraphs restates the actions required by
paragraph (g) of AD 2011-23-06, Amendment 39-
16857 (76 FR 68304, November 4, 2011). For
Sicma Aero Seat Model 9401, 9402, 9404, 9406,
9407, 9408, and 9409 series passenger seat
assemblies: Within 6 months after November 21,
2011 (the effective date of AD 2011-23-06),
perform a detailed inspection for cracking of the
central and lateral spreaders of the affected
seats, in accordance with paragraph 2/A1.,
''Checking procedures of lateral and central
spreaders,'' of the Accomplishment Instructions
of Sicma Aero Seat Service Bulletin 94-25-013,
Issue 4, dated February 12, 2008.
(1) If no cracking is found on any central
spreader, repeat the detailed inspection
thereafter at intervals not to exceed 550 flight
hours until the replacement specified in
paragraph (i) of this AD is done.
(2) If no cracking or only cracks that are shorter
than 8 millimeters (mm) (0.315 inch) are found
on any lateral spreader, repeat the detailed
inspection thereafter at intervals not to exceed
550 flight hours until the replacement specified
in paragraph (i) of this AD is done.
(3) If all cracks found on any central spreader are
shorter than 8 mm (0.315 inch), before further
flight, repair the affected spreader, in
accordance with paragraphs 2/A through C2. of
the Accomplishment Instructions of Sicma Aero
Seat Service Bulletin 94-25-011, Revision 3, dated
June 30, 2008. Within 550 flight hours after doing
the repair, do the detailed inspection specified in
paragraph (g) of this AD, and repeat the
inspection thereafter at intervals not to exceed
Sicma Aero Seat Service Bulletin
94-25-012, Revision 1, dated
June 26, 2008.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/AN/A by P/N installed. This AD
supersedes AD 2011-23-06
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CommutAir
S/N
554
FAA TC Hours Cycles Date Hours Cycles Date Hours Cycles Date
DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
######## -- 34, Navigation. 6/16/15
This AD applies to Zodiac Aerotechnics
(formerly Intertechnique Aircraft
Systems) flightcrew oxygen mask
regulators, all part number (P/N) MA10,
MC10, MC20, MF10, MF20, MLC20,
MLD20, MRA005, MRA022, and MRA023
series; certificated in any category;
installed on, but not limited to, airplanes
manufactured by Airbus, ATR, BAE
Systems (Type Certificate previously held
by British Aerospace), Boeing,
Bombardier (Type Certificate previously
held by Canadair, De Havilland Canada),
Cessna, Dassault, EADS CASA, EMBRAER,
Gulfstream, Hawker Beechcraft (Type
Certificate previously held by Raytheon,
Beech), Israel Aircraft Industries (IAI),
McDonnell Douglas, Piaggio, Pilatus,
Piper, and SOCATA.
Except as provided by paragraph (i) of this AD:
Within 24 months after the effective date of this
AD, inspect the inflatable harness fitted to each
flightcrew oxygen mask regulator to determine if
the inflatable harness is installed with a part
number and a batch number identified in
Appendix I of Zodiac Aerospace Service Bulletin
MXH-35-240, Revision 7, dated September 1,
2011 (for all 11 airplanes other than Bombardier
airplanes); or Appendix I of Zodiac Aerospace
Service Bulletin MXH-35-241, Revision 3, dated
June 23, 2011 (for Bombardier airplanes).
Note 1 to paragraph (g) of this AD: Referring only
to Appendix II of Zodiac Aerospace Service
Bulletin MXH-35-240, Revision 7, dated
September 1, 2011; or Appendix II of Zodiac
Aerospace Service Bulletin MXH-35-241, Revision
3, dated June 23, 2011; to identify a specific
oxygen mask regulator is insufficient to
demonstrate that the inflatable harness fitted to
that oxygen mask regulator is not listed in
Appendix I of Zodiac Aerospace Service Bulletin
MXH-35-240, Revision 7, dated September 1,
2011; or Appendix I of Zodiac Aerospace Service
Bulletin MXH-35-241, Revision 3, dated June 23,
2011.
Within 24 months after the
effective date of this AD, replace
the inflatable harness with a new
or re-identified harness, in
accordance with the
Accomplishment Instructions of
Zodiac Aerospace Service
Bulletin MXH-35-240, Revision 7,
dated September 1, 2011 (for all
airplanes other than Bombardier
airplanes); or Zodiac Aerospace
Service Bulletin MXH-35-241,
Revision 3, dated June 23, 2011
(for Bombardier airplanes).
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A by P/N installed
10 of 11 11/8/2017
CommutAir
S/N
554
FAA TC Hours Cycles Date Hours Cycles Date Hours Cycles Date
DHC 8-Q311 - MSN 554 - N837CA - Maintenance History
AIRWORTHINESS DIRECTIVES - APPLIANCES STATUS REPORT
DoneFrequency
Subject
A/C Register Type
8-Nov-178-Nov-17
DUE
Today's
DATE:
Remarks
Last A/C Status
Update DATE:CSNTSN
3533532131.20N837CA DASH 8-311
Efective
DateMeans of Compliance
Directives
Applicability StatusTerminating Actions
######## --
Joint Aircraft System
Component (JASC)/Air
Transport Association
(ATA) of America Code
35; Oxygen.
7/15/16
This AD applies to B/E Aerospace
Protective Breathing Equipment (PBE),
part number (P/N)
119003-11, that is installed on airplanes.
(g) Inspection Within 3 months after July 15,
2016 (the effective date of this AD), while still in
the stowage box, physically inspect the PBE
pouch to determine if it has an intact vacuum
seal. Do this inspection following paragraph
III.A.1. of the Accomplishment Instructions in B/E
Aerospace Service Bulletin No. 119003-35-011,
Rev. 000, dated February 4, 2015.
(h) Replacement (1) If a PBE pouch is found that
does not have an intact vacuum seal during the
inspection required in paragraph (g) of this AD:
Before further flight or following existing
minimum equipment list (MEL) procedures,
replace the PBE with a PBE, P/N 119003-21,
following paragraphs III.C., III.D.(4), III.D.(6), and
III.D.(7) of the Accomplishment Instructions in
B/E Aerospace Service Bulletin No. 119003-35-
009, Rev. 001, dated April 12, 2016, or replace it
with another FAAapproved serviceable PBE. (2) If
a PBE pouch is found during the inspection
required in paragraph (g) of this AD where the
vacuum seal is intact: Within 18 months after
July 15, 2016 (the effective date of this AD),
remove
PBE, P/N 119003-11, and replace the PBE with
PBE, P/N 119003-21, following paragraphs III.C.,
III.D.(4), III.D.(6), and III.D.(7) of the
Accomplishment Instructions in B/E Aerospace
Service Bulletin No. 119003-35-009, Rev. 001,
dated April 12, 2016, or replace it with another
FAAapproved serviceable PBE.
(h) Replacement
(1) If a PBE pouch is found that
does not have an intact vacuum
seal during the inspection
required in paragraph (g) of this
AD: Before further flight or
following existing minimum
equipment list (MEL) procedures,
replace the PBE with a PBE, P/N
119003-21, following paragraphs
III.C., III.D.(4), III.D.(6), and
III.D.(7) of the Accomplishment
Instructions in B/E Aerospace
Service Bulletin No. 119003-35-
009, Rev. 001, dated April 12,
2016, or replace it with another
FAAapproved serviceable PBE.
(2) If a PBE pouch is found during
the inspection required in
paragraph (g) of this AD where
the vacuum seal is intact:Within
18 months after July 15, 2016
(the effective date of this AD),
remove PBE, P/N 119003-11, and
replace the PBE with PBE, P/N
119003-21, following paragraphs
III.C., III.D.(4), III.D.(6), and
III.D.(7) of the Accomplishment
Instructions in B/E Aerospace
Service Bulletin No. 119003-35-
009, Rev. 001, dated April 12,
2016, or replace it with another
FAAapproved serviceable PBE.
N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A by P/N installed
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