CommutAir - Airstream International Group LtdFalcon 900 airplanes Canadair Challenger CL-601 airplanes British Aerospace HS 125-700A airplanes Beechcraft 300 series airplanes Within

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

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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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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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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


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.


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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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.


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 by Model Number. APU

APS500/T-62-T-40C7B/167301-

101A installed on aircraft

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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.


AD, inspect to determine the serial number of

the PBE units installed in the aircraft, in


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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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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Directives


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



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


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


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

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######## --

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



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


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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Directives


######## -- 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


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).


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Directives


######## --

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


(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



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