Cessna 210 Series - Civil Aviation Authority of New Zealand

Cessna 210 Series - Civil Aviation Authority of New Zealand
Airworthiness Directive Schedule
Aeroplanes
Cessna 210 Series
22 October 2015
Notes
1.
This AD schedule is applicable to Cessna 210, 210-5A (205A), 210G, 210L, 210M,
210N, 210R, P210N, T210N and T210R series aircraft manufactured under Federal
Aviation Administration (FAA) Type Certificate No. 3A21.
2.
The Federal Aviation Administration (FAA) is the National Airworthiness Authority
(NAA) responsible for the issue of State of Design Airworthiness Directives (ADs) for
Cessna 210 series aircraft. State of Design ADs applicable to these aircraft can be
obtained directly from the FAA web site. The link to the FAA web site is available on
the CAA web site at
http://www.caa.govt.nz/Airworthiness_Directives/states_of_design.html
3.
The date above indicates the amendment date of this schedule.
4.
New or amended ADs are shown with an asterisk *
Contents
DCA/CESS210/1 Main Gear - Wheel Assembly Through Bolts - Inspection and Modification ....................... 3
DCA/CESS210/2 Cancelled – FAA AD 72-07-09 refers.................................................................................. 3
DCA/CESS210/3 Main Gear - Wheel Assembly Cap Screws - Inspection and Modification .......................... 3
DCA/CESS210/4 Mainplane Rear Spar - Inspection....................................................................................... 4
DCA/CESS210/5 Flap Actuator Jack Screw - Modification and Inspection..................................................... 4
DCA/CESS210/6A Turbocharger - Nameplate and Centre Housing - Inspection and Replacement .............. 4
DCA/CESS210/7 Fuel Selector Valve - Inspection ......................................................................................... 5
DCA/CESS210/8 Flexible Fuel Tanks - Inspection ......................................................................................... 5
DCA/CESS210/9 Fuel Cap - Modification ....................................................................................................... 5
DCA/CESS210/10 Electrical System - Modification ........................................................................................ 6
DCA/CESS210/11 Fuel System Operation - Placard ...................................................................................... 6
DCA/CESS210/12 Alternator Installation - Modification and Inspection ......................................................... 6
DCA/CESS210/13 Fuel System - Modification ................................................................................................ 7
DCA/CESS210/14 Turbo Charger Installation - Inspection and Removal ....................................................... 7
DCA/CESS210/15 Vacuum Pump Installation - Modification .......................................................................... 7
DCA/CESS210/16 Fuel Selector Valve - Inspection and Modification ............................................................ 8
DCA/CESS210/17 Induction Airbox Duct - Inspection and Repair .................................................................. 8
DCA/CESS210/18A Fuel Tank/Reservoir Drains – Modification and Flight Manual Revision......................... 8
DCA/CESS210/19 Exhaust Manifold Heat Exchanger - Inspection ................................................................ 9
DCA/CESS210/20A Cancelled – DCA/CESS210/41 refers ............................................................................ 9
DCA/CESS210/21 Engine Compartment Hoses - Inspection and Replacement ............................................ 9
DCA/CESS210/22 Electrical Wire Bundle/Fuel Line - Clearance ................................................................. 10
DCA/CESS210/23 Air Induction Hose - Replacement .................................................................................. 11
DCA/CESS210/24 Fuel System - Calibration and Modification..................................................................... 11
DCA/CESS210/25 Lower Forward Doorpost and Strut Fitting - Inspection ................................................... 11
DCA/CESS210/26 Bladder Type Fuel Cells - Inspection And Modification................................................... 12
DCA/CESS210/27 Number 5 Cylinder Baffle - Modification.......................................................................... 12
DCA/CESS210/28 Fuel, Oil or Hydraulic Hose - Removal ............................................................................ 12
DCA/CESS210/29 Severe Icing Conditions - Flight Manual Revision........................................................... 13
DCA/CESS210/30 Severe Icing Conditions - Flight Manual Revision........................................................... 14
DCA/CESS210/31 Fuel Strainer Assembly – Inspection .............................................................................. 16
DCA/CESS210/32 Horizontal Stabiliser Brackets – Inspection and Replacement ....................................... 16
DCA/CESS210/33 Shoulder Harness – Inspection & Modification ............................................................... 17
Issued 22 October 2015
Page 1 of 26
CAA of NZ
DCA/CESS210/34 Alternate Static Source Selector – Inspection ................................................................. 18
DCA/CESS210/35 Alternate Static Source Selector – Inspection ................................................................. 19
DCA/CESS210/36 Engine Compartment Flexible Hoses – Inspection and Replacement ............................ 20
DCA/CESS210/37
Main Landing Gear Saddles – Inspection and Replacement ......................................... 20
DCA/CESS210/38 Fuel Quantity System – Inspection and Rework ............................................................. 23
DCA/CESS210/39 Throttle and Mixture Controls – Inspection and Modification .......................................... 24
DCA/CESS210/40 Engine Controls – Inspection and Rework ...................................................................... 24
DCA/CESS210/41 Seat Adjustment Mechanism – Inspection and Replacement ......................................... 24
DCA/CESS210/42 Main Spars – Inspection and Replacement .................................................................... 25
From 1 October 2012 the Civil Aviation Authority of New Zealand (CAA) will no longer rewrite the text of
State of Design ADs. Applicable State of Design ADs will be listed below and can be obtained directly
from the National Airworthiness Authority (NAA) web site. The link to the NAA web site is available on
the CAA web site at http://www.caa.govt.nz/Airworthiness_Directives/states_of_design.html If additional
NZ ADs need to be issued when an unsafe condition is found to exist in an aircraft or aeronautical
product in NZ they will be added to the list below............................................................................................. 26
72-07-09
Cancelled – DCA/CESS210/43 refers ........................................................................................ 26
* DCA/CESS210/43B Vertical Stabiliser – Inspection ................................................................................... 26
Issued 22 October 2015
Page 2 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
DCA/CESS210/1
Main Gear - Wheel Assembly Through Bolts - Inspection and Modification
Applicability:
Model 210 series aircraft, S/N 21060090 through to 21060319.
Requirement:
Accomplish the following:
1. Inspect main gear wheel assemblies for broken through bolts. Replace broken
bolts with serviceable bolts of the same type or modify as follows.
2. Modify main gear wheel assemblies by incorporating Cessna Parts Kit P/N PL30403 in accordance with Cessna SESL 74-8 & Supl. 1.
Compliance:
Modification shall be incorporated not later than 31 August 1974.
Effective Date:
6 June 1974
DCA/CESS210/2
Effective Date:
Cancelled – FAA AD 72-07-09 refers
26 February 2015
DCA/CESS210/3
Main Gear - Wheel Assembly Cap Screws - Inspection and Modification
Applicability:
All model 210 series aircraft fitted with McCauley wheels P/N D-30291 and wheels
modified per DCA/CESS210/1.
Requirement:
As a result of a local failure accomplish the following:
1. (a) Dismantle each wheel and inspect the six tapped holes in each side of the hub
for evidence of thread distress.
(b) Inspect the area around each hole for cracks using a dye penetrant method.
(c) Reject any hub with damaged threads or cracks.
(d) Reassemble in accordance with McCauley SB WB-1-A (Cessna SESL SE 74-8 &
Supl. 1 refers) but use lock washers P/N AN935-516 under the heads of the cap
screws instead of plain washers P/N A-1638-1.
2. (a) Check that each socket head cap screw torque is within range 190 lb. in. to
200 lb. in.
(b) If any cap screw is less than 190 lb. in. repeat 1 above and report the defect to the
Director of the Civil Aviation Authority.
Compliance:
1. Within the next 10 hours TIS.
2. At intervals not to exceed 50 hours TIS.
Effective Date:
1 November 1974
Issued 22 October 2015
Page 3 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
DCA/CESS210/4
Applicability:
Mainplane Rear Spar - Inspection
All model 205 series aircraft, all S/N except those aircraft fitted with rear spar P/N
0523400-90 and 91, or P/N 0523400-111 and -112.
All model 210 series aircraft, aircraft except those with a cantilever wing.
Requirement:
1. Examine each mainplane rear spar for cracks in the area of the root attachment
fitting. Cracking originates around the spar web radius below the root end fitting, and
may extend to the spar upper flange at the outboard end of the root fitting where the
reinforcing angle is joggled.
2. The rear spar web may be examined after the wing root lower fairings are
removed. If a crack is present it may be obscured by the root ribs and the spar root
end fittings. Careful inspection should be made of the inboard edge and radius of the
spar web visible below the root fittings and inboard of the root ribs. The edge of the
rear spar upper flange should be inspected through the inboard inspection hole behind
the rear spar. Where doubt exists, the trailing edge root end rib shall be removed to
permit a more detailed inspection.
Compliance:
1. Unless already accomplished, within the next 100 hours TIS and thereafter at
intervals not exceeding 100 hours TIS.
2. Immediately following any case of mainplane damage or ground looping.
Effective Date:
2 June 1975
DCA/CESS210/5
Applicability:
Flap Actuator Jack Screw - Modification and Inspection
Model 210 series aircraft, S/N 21058221 through to 21058818
Model T210 series aircraft, S/N T210-0001 through to T210-0197
Requirement:
Comply with the requirements in Cessna Service Letter SE72-2 dated 21 Jan 1972
and Cessna SL SE72-2 Supplement 1 dated 24 March 1972, or later FAA approved
revisions.
(FAA AD 72-03-03R3)
Compliance:
1. Modification: By 31 October 1975.
2. Inspection: Every 100 hours TIS or annually post modification.
Effective Date:
30 September 1975
DCA/CESS210/6A
Replacement
Turbocharger - Nameplate and Centre Housing - Inspection and
Applicability:
Model T210 series aircraft, S/N T210-0001 through to T210-0454 and S/N 21059200
through to 21061758.
Requirement:
Comply with Cessna SESL SE 77-3 & Supl. 2 & 3 and SESL 77-42.
(FAA AD 78-07-01 refers)
Compliance:
Within the next 25 hours TIS unless already accomplished.
Effective Date:
DCA/CESS210/6 - 16 March 1977
DCA/CESS210/6A - 21 July 1978
Issued 22 October 2015
Page 4 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
DCA/CESS210/7
Applicability:
Fuel Selector Valve - Inspection
Model 205 series aircraft, which have had valves replaced,
Model 210 series aircraft, S/N 21061155 through to 21062043 with a fuel selector
valve S/N 1421 through to 3269,
OR earlier aircraft having had the fuel selector valve replaced
Requirement:
Comply with Cessna SESL Se 77-22.
(FAA AD 77-16-05 refers)
Compliance:
Within the next 25 hours TIS unless already accomplished
Effective Date:
16 September 1977
DCA/CESS210/8
Applicability:
Flexible Fuel Tanks - Inspection
Model 205 Series aircraft, S/N 205-0001 through to 205-0577,
Model 210 Series aircraft, S/N 21057841 through to 21058818,
Model T210 Series aircraft, S/N T210-0001 through to T210-0197,
OR any other model 205, 210 or T210 aircraft equipped with Goodyear BTC-39 series
aircraft, fuel tanks
Requirement:
Accomplish the following:
1. Visual inspection per Part A of Cessna SESL SE 78-10 & Supl. 1.
2. Detailed inspection per Part B of Cessna SESL SE 78-10 & Supl. 1 followed by
Part C as necessary.
(Goodyear SB FT-77-1 and FAA AD 78-05-06 also refer)
Compliance:
1. Within the next 25 hours TIS or 30 days whichever is the sooner.
2. Within the next 100 hours TIS or 6 months whichever is the sooner, thereafter at
intervals not exceeding 12 months, until replaced.
Effective Date:
28 April 1978
DCA/CESS210/9
Applicability:
Fuel Cap - Modification
Model 205 series aircraft, S/N 205-0001 through to 205-0577
Model 210 series aircraft, S/N 21057001 through to 21059361
Model T210 series aircraft, S/N T210-0001 through to T210-0454
Requirement:
Fit vented fuel caps with related adapters and fuel servicing placards per Cessna SEB
92-27.
(FAA AD 79-10-14 R1 refers)
Compliance:
Within the next 100 hours TIS unless already accomplished.
Effective Date:
23 March 1979
Issued 22 October 2015
Page 5 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
DCA/CESS210/10
Applicability:
Electrical System - Modification
Model 205 series aircraft, S/N 205-0320 through to 205-0577
Model 210 series aircraft, S/N 21058162 through to 21061039
Model T210 series aircraft, S/N T210-0001 through to T210-0454
Requirement:
To prevent inflight electrical system failure, smoke in cockpit and/or fire in wire bundle
behind instrument panel, accomplished the following:
Disconnect at ammeter or electrical system bus, as applicable, wire which connects
bus to cigar lighter receptacle (wire is connected to either the bus side, or equipment
side of a circuit breaker, or to the ammeter) then either:
1. Reconnect wire to bus using an existing or newly installed circuit protection device
properly rated for wire gauge used, or
2. disconnect wire from lighter receptacle and remove it from aircraft, or
3. insulate disconnected end of wire and secure it to bundle in which it is routed.
(FAA AD 79-08-03 refers)
Note:
FAA AC 43.13-1A contains guidance information on wire gauge/circuit protection
device ratings
Compliance:
Within next 100 hours TIS
Effective Date:
29 June 1979
DCA/CESS210/11
Applicability:
Fuel System Operation - Placard
Model 205 series aircraft, S/N 205-0001 through to 205-0555 with SK205-5 installed
and S/N 205-0556 through to 205-0577,
Model 210 series aircraft, S/N 21057841 through to 21058351 with SK205-5 OR
SK206-2 installed and S/N 21058352 through to 21063426 as detailed in Cessna SIL
SE 79-25 Supl. 1,
Model T210 series aircraft, S/N T210-0001 through to T210-0454
Model P210 series aircraft, S/N P21000001 through to P21000292 as detailed in SL.
Requirement:
Install placard and special procedure card per Cessna SIL SE 79-25 Supl. 1.
(FAA AD 79-15-01 refers)
Compliance:
By 30 September 1979
Effective Date:
31 August 1979
DCA/CESS210/12
Applicability:
Alternator Installation - Modification and Inspection
Model 210 series aircraft, S/N 21058783 through to 21062666,
Model T210 series aircraft, S/N T210-0001 through to T210-0454,
Model P210 series aircraft, S/N P21000001 through to P21000026.
Requirement:
1. Install either additional ground strap per Cessna SESIL SE 79-59 or embody
Cessna service kit SK-210-84 per SESIL SE 79-5.
2. Visually inspect alternator installation for, and if necessary provide, at least ½ inch
clearance between alternator and adjacent flammable fluid carrying lines, power plant
controls and electrical wiring.
Issued 22 October 2015
Page 6 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
3. Visually inspect existing alternator to airframe ground for proper installation (SE 7959 view A-A refers), evidence of looseness at the terminal and adequate length to
allow for relative motion between alternator and airframe. Also, confirm that ground
straps between engine and airframe mount are installed and provide continuity
between engine and mount. Correct any unsatisfactory conditions found per FAA AC
43.13-1A.
(FAA AD 79-25-07 refers)
Compliance:
Within the next 50 hours TIS unless already accomplished.
Effective Date:
8 February 1980
DCA/CESS210/13
Applicability:
Fuel System - Modification
Model T210 series aircraft, S/N 21061040 through to 21063660,
Model P210 series aircraft, S/N P21000001 through to P21000389.
Requirement:
Modify engine compartment fuel system per Cessna SESIL SE 79-60 & Supl. 1
Compliance:
Within the next 100 hours TIS
Effective Date:
21 March 1980
DCA/CESS210/14
Applicability:
Turbo Charger Installation - Inspection and Removal
Model 210 series aircraft, S/N 21059200 through to 21063954 and 21058140,
Model T210 series aircraft, S/N T210-0001 through to T210-0454,
Requirement:
Inspect per Cessna SESIL SE 80-24 and remove from service any AIRESEARCH
TURBOCHARGER with S/N HI 0101 through HI 0175 as specified.
(FAA AD 80-07-01 refers)
Compliance:
Within the next 10 hours TIS unless already accomplished
Effective Date:
6 June 1980
DCA/CESS210/15
Applicability:
Vacuum Pump Installation - Modification
Model 210 Series aircraft, and T210 S/N 21059810 through 21064535, and
Model P210 Series aircraft, S/N P21000001 through P21000760, and
Fitted with Airborne model 442 CW-8 vacuum pump, pneumatic de-icer boots and
vacuum operated attitude indicator.
Requirement:
Modify per Cessna SESIL SE 82-13 Supl. 1.
(FAA AD 82-06-10 refers)
Compliance:
Prior to IFR flight.
Effective Date:
28 May 1982
Issued 22 October 2015
Page 7 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
DCA/CESS210/16
Applicability:
Fuel Selector Valve - Inspection and Modification
Model 205 series aircraft, S/N 205-0001 through to 205-0577
Model 210 series aircraft, S/N 21058819 through to 21064535
Model T210 series aircraft, S/N T210-0198 through to T210-0454
Model P210 series aircraft, S/N P21000001 through to P21000760
Requirement:
1. Visually inspect fuel selection for free play. Renew worn or loose parts as
necessary to ensure free play does not exceed 15 degrees.
2. Safety wire selector valve shaft to yoke roll pin per Cessna SIL SE 84-5.
(FAA AD 85-02-07 refers)
Compliance:
Within the next 100 hours TIS.
Effective Date:
22 March 1985
DCA/CESS210/17
Induction Airbox Duct - Inspection and Repair
Applicability:
Models 210 series aircraft, S/N 21058221 through to 21064226
Requirement:
1. Visually inspect engine induction airbox outboard duct lower skin for cracks.
2. If cracks are found, before further flight either,
(a) replace duct with Cessna P/N 1250705 duct, or
(b) repair cracked duct using material at least .040 inch thick.
(FAA AD 85-10-02 refers)
Compliance:
Inspect within the next 100 hours TIS and thereafter at intervals not exceeding 100
hours TIS until duct repaired or replaced.
Effective Date:
2 August 1985
DCA/CESS210/18A
Applicability:
Fuel Tank/Reservoir Drains – Modification and Flight Manual Revision
Model 210B through to 210R series aircraft, and
Model T210F through to T210R series aircraft, and
Model P210N and P210R, and
Fitted with fuel reservoir(s).
Requirement:
To preclude possible power loss or engine stoppage due to fuel contamination,
accomplish the following:1. For models 210G, T210G through 210L and T210L (S/N 21058819 through
21060539 and T210-0198 through T2100454), install quick drains in wing fuel tanks
and reservoirs per Cessna SIL SE 79-45 and SE 84-8, or by using equivalent aircraft
standard hardware.
2. For models 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L,
210M, 210N, 210R, T210F, T210G, T210H, T210J, T210K, T210L, T210M, T210N,
T210R (S/N 21057841 and on) P210N and P210R (S/N P21000001 and on) insert the
following paragraphs into the aircraft flight manual. Alternatively, a manufacturer’s
flight manual revision with the same wording is acceptable.
(FAA AD 86-19-11 refers)
Issued 22 October 2015
Page 8 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
PILOT OPERATING PROCEDURES - PREFLIGHT FUEL SYSTEM CHECK
Fuel sampling: Fuel strainer, wing tank and reservoir quick drains.
1. Place a suitable container under the fuel strainer drain outlet prior to operating the
strainer drain control for at least 4 seconds. Check strainer drain closed.
2. Inspect the fluid drained from the fuel strainer and each wing tank quick drain for
evidence of fuel contamination in the form of water, rust, sludge, ice or any other
substance not compatible with fuel. Also check for proper fuel grade before the first
flight of each day and after each refueling. If any contamination is detected, comply
with 4 below.
3. Repeat Steps 1 and 2 on each wing tank quick drain.
4. If the aircraft has been exposed to rain, sleet or snow, or if the wing fuel tanks or
fuel strainer drains produce water, the fuel reservoir(s) must be checked for the
presence of water by operating the fuel reservoir quick drains. The aircraft fuel system
must be purged to the extent necessary to insure that there is no water, ice or other
fuel contamination.
NOTE 1: The fuel reservoir(s) are located under the fuselage between the firewall and
forward door post on all airplane models. Consult the pilots Aircraft Flight Manual,
Operating Handbook or Owners Manual in order to determine if one or two
reservoir(s) are installed.
NOTE 2: A check for the presence of water using the fuel reservoir quick drains prior
to the first flight of each day is considered good operating practice.
DCA/CESS210/18A refers
Compliance:
1. Within next 100 hours TIS.
2. By 1 February 2000
Effective Date:
DCA/CESS210/18 - 14 November 1986
DCA/CESS210/18A - 19 November 1999
DCA/CESS210/19
Exhaust Manifold Heat Exchanger - Inspection
Applicability:
Model 210 Series aircraft, S/N 210-59200 through 210-64897
Model T210 Series aircraft, S/N T210-0001 through S/N T210-0454
Requirement:
To prevent exhaust gases entering cabin, inspect per Cessna SL SE 71-11. Repair
defective installations before further.
(FAA AD 71-09-07 refers)
Compliance:
At intervals not exceeding 100 hours TIS
Effective Date:
13 February 1987
DCA/CESS210/20A
Effective Date:
30 June 2011
DCA/CESS210/21
Applicability:
Cancelled – DCA/CESS210/41 refers
Engine Compartment Hoses - Inspection and Replacement
Model 210 series aircraft, S/N 21059200 through to 21064781 fitted with turbo
chargers, and
Model T210 series aircraft, S/N T210-00001 through to T210-0454
Issued 22 October 2015
Page 9 of 26
CAA of NZ
Aeroplanes
Requirement:
Cessna 210 Series
To prevent possible power loss or fire due to failure of certain Aeroquip 601 hose
assemblies accomplish the following:
1. Visually inspect all exterior metal bonded flex hose assemblies, including fire
sleeve hose assemblies, in engine compartment. If Aeroquip P/N AE 701 appears on
identification tag, no further action required.
2. If tag displays model/part no. suffix 601, following action required:
(a) Determine whether hose is identified with a cure date 1Q84 through 3Q87 (Cure
date refers to the quarter and year of manufacture).
(b) Check aircraft records for engine compartment model 601 hose replacement
between April, 1984 and May, 1988.
(c) If any engine compartment model 601 hose displays a cure date of 1Q84 through
3Q87, or there is no cure date tag, or records indicate that a model 601 hose was
installed between April 1984 and May 1988, replace suspect hoses, as follows:
(i) Replace wastegate supply hose assembly, Aeroquip P/N 601000-4-0310, or hose
identified as Cessna S1236-4-0310 supplied by sources other than Cessna, or as
identified above, with an Aeroquip P/N AE 3663162E0310 hose or equivalent per
Cessna SEB 88-5 or with an Aeroquip 601000-4-0310 hose assembly displaying a
cure date of 4Q87 or subsequent.
3. Replace all other suspect Aeroquip 601 type hose assemblies in engine
compartment with serviceable hoses displaying a cure date of 4Q87 or subsequent).
(FAA AD 88-22-07 refers)
Compliance:
1. Inspection - within the next 50 hours TIS.
2. Replacement of suspect wastegate hoses - before further flight.
3. Replacement of all other suspect hoses - within next 12 months
Effective Date:
10 March 1989
DCA/CESS210/22
Applicability:
Electrical Wire Bundle/Fuel Line - Clearance
Model 210 series aircraft, S/N 21059062 through to 21064535
Model T210 series aircraft, S/N T210-0393 through to T210-0454
Model P210 series aircraft, S/N P21000001 through to P21000760
Requirement:
To prevent fuel leakage caused by damaged fuel lines, which could result in an inflight fire, accomplish the following:
1. Inspect the electrical wires in the nose gear tunnel area and the fuel line to the
engine-driven fuel pump for cracks or chafing. Renew any electrical wire or fuel line
found cracked or chafed before further flight.
2. Ensure that the electrical wires are bundled and route or clamp the wire bundle so
that there is a clearance of at least 6mm (0.25 inches) between the wire bundle and
the fuel line.
Note:
Cessna SIL SE 82-32 highlights the inspection area referenced in this AD.
(FAA AD 91-22-01 refers)
Compliance:
Within the next 50 hours TIS
Effective Date:
29 November 1991
Issued 22 October 2015
Page 10 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
DCA/CESS210/23
Air Induction Hose - Replacement
Applicability:
Model T210 series aircraft, modified by STC SA2231CE and STC SA3203NM.
Requirement:
To prevent air induction hose failure visually inspect between the turbocharger and
intercooler to determine whether a Gates air induction hose, P/N 20987 or 21370 is
installed. If a Gates hose is installed, before further flight accomplish the following:1. Loosen the two AN737-TW clamps and remove the Gates hose.
2. Install The Aircraftsman hose, P/N MW1118, and tighten the two AN737-TW
clamps.
(FAA AD 93-13-09 refers)
Compliance:
Within the next 50 hours TIS.
Effective Date:
3 September 1993
DCA/CESS210/24
Applicability:
Fuel System - Calibration and Modification
Model 210 series aircraft, S/N 21058819 through to 21065009,
Model T210 series aircraft, S/N T210-0198 through to T210-0454,
Model P210 series aircraft, S/N P21000001 through to P21000874.
Requirement:
To prevent loss of engine power caused by inadvertent fuel loss or inadequate
refuelling accomplish the following:1. Calibrate the fuel quantity indication system at the unusable (empty) fuel gauge
indication by:
(i) Draining the wing fuel tank sumps (defuel the aircraft).
(ii) Turning the master switch on, ensure that the fuel gauges indicate empty ("E").
(iii) Adjust or replace the transmitter or gauge, as required to obtain the proper
"empty" indication with empty wing fuel tanks.
2. Install raised fuel caps per Cessna SEB91-10 Revision 1 or per STC SA2456CE.
(FAA AD 94-12-08 refers)
Compliance:
By 2 September 1995.
Effective Date:
2 September 1994
DCA/CESS210/25
Lower Forward Doorpost and Strut Fitting - Inspection
Applicability
Model 210-5 (205) series aircraft, S/N 205-0551, -0556 through to -0577.
Requirement:
To prevent failure of the lower cabin doorpost and loss of aircraft structural integrity,
accomplish the following:Inspect the lower area of the forward cabin doorposts for cracks per Cessna SEB 935, revision 1. If a crack is found, before further flight, modify the doorposts by installing
a service kit per SEB 93-5, revision 1.
Compliance:
Inspect within next 100 hours TIS and thereafter at intervals not to exceed 500 hours
TIS, until modified per SEB 93-5, revision 1.
Effective Date:
7 June 1996
Issued 22 October 2015
Page 11 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
DCA/CESS210/26
Applicability:
Bladder Type Fuel Cells - Inspection And Modification
Model 205 series aircraft, S/N 205-0001 through to 205-0577
Models 210 series aircraft, S/N 210-57001 through to 21058818
Model T210 series aircraft, S/N P210-0001 through to P210-0197
Requirement:
To preclude possible power loss or engine stoppage due to water contamination of
fuel system, accomplish the following:
1. Inspect fuel tank filler areas and caps for proper sealing, check fuel cap seal by
actuating locking tab and noting that force is maintained between cap seal and
adaptor when tab is in over-centre locked position, or accomplish leak test per Cessna
SIL SE 82-34.
Note 1:
No longer required when raised neck fuel caps installed per Cessna SK 182-85 (SIL
SE 84-16 refers)
2. Inspect fuel cell for wrinkles per Cessna SIL SE 84-4. If wrinkles found, modify
and rework fuel cell per Cessna SIL SE 84-9 within next 100 hours TIS.
Note 2:
No longer required when modification embodied.
3. Install quick drains in fuel tank sumps and reservoirs where applicable, per Cessna
SIL SE 84-9.
(FAA AD 84-10-01 R1 refers)
Compliance:
1. Inspection - within next 50 hours TIS and thereafter at intervals not exceeding 12
months.
2. Inspection - within next 50 hours TIS and thereafter at intervals not exceeding 12
months.
3. Modification - within next 100 hours TIS.
Effective Date:
20 December 1996
DCA/CESS210/27
Applicability:
Number 5 Cylinder Baffle - Modification
Model 205 series aircraft, S/N 205-0001 through to 205-0566,
Model 210 series aircraft, S/N 210-00001 through to 21058395
Requirement:
Comply with Cessna SL 64-32
Compliance:
Within the next 100 hours TIS.
Effective Date:
20 December 1996
DCA/CESS210/28
Fuel, Oil or Hydraulic Hose - Removal
Applicability:
Model 205 and 210 series aircraft, all S/N.
Requirement:
To prevent fuel, oil or hydraulic systems failure caused by a collapsed hose, check the
aircraft maintenance records for any fuel, oil or hydraulic hose, Cessna P/N S51-10,
replaced between March 1995 and 14 March 1997. If any fuel, oil or hydraulic hose,
Cessna P/N S51-10, has been replaced between March 1995 and 14 March 1997,
accomplish the following:Before further flight physically check for a diagonal or spiral external reinforcement
wrap per Cessna SB SEB96-15. Replace any P/N S51-10 hose that has a diagonal or
spiral pattern external reinforcement wrap with a P/N S51-10 hose that has a crisscross pattern external wrap per SB SEB96-15.
Issued 22 October 2015
Page 12 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
(FAA AD 97-01-13 refers)
Compliance:
Within next 60 hours TIS or 60 days, whichever is the sooner.
Effective Date:
14 March 1997
DCA/CESS210/29
Applicability:
Severe Icing Conditions - Flight Manual Revision
Model T210N aircraft, S/N 21063641 through to 21064897,
Model P210N aircraft, S/N P21000386 through to P21000834,
Model P210R aircraft, all S/N.
Requirement:
To minimise the potential hazards associated with operating the aircraft in severe icing
conditions (by providing more clearly defined procedures and limitations associated
with such conditions), incorporate the following into the Aircraft Flight Manual (AFM):1. Limitations Section of the Aircraft Flight Manual
“WARNING
Severe icing may result from environmental conditions outside of those for which the
aircraft is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions
(supercooled liquid water and ice crystals) may result in ice build-up on protected
surfaces exceeding the capability of the ice protection system, or may result in ice
forming aft of the protected surfaces. This ice may not be shed using the ice
protection systems, and may seriously degrade the performance and controllability of
the aircraft.
•
During flight, severe icing conditions that exceed those for which the aircraft is
certificated shall be determined by the following visual cues. If one or more of these
visual cues exists, immediately request priority handling from Air Traffic Control to
facilitate a route or an altitude change to exit the icing conditions.
Unusually extensive ice accumulation on the airframe and windshield in areas
not normally observed to collect ice.
-
Accumulation of ice on the upper surface of the wing aft of the protected area.
Accumulation of ice on the engine nacelles and propeller spinners farther aft
than normally observed.
•
Since the autopilot, when installed and operating, may mask tactile cues that
indicate adverse changes in handling characteristics, use of the autopilot is prohibited
when any of the visual cues specified above exist, or when unusual lateral trim
requirements or autopilot trim warnings are encountered while the aircraft is in icing
conditions.
•
All wing icing inspection lights must be operative prior to flight into known or
forecast icing conditions at night. This supersedes any relief provided by the Master
Minimum Equipment List (MMEL).”
2. Normal Procedures Section of the Aircraft Flight Manual
“THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE
IN-FLIGHT ICING:
• Visible rain at temperatures below 0 degrees Celsius ambient air temperature.
• Droplets that splash or splatter on impact at temperatures below 0 degrees Celsius
ambient air temperature.
Issued 22 October 2015
Page 13 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
PROCEDURES FOR EXITINGTHE SEVERE ICING ENVIRONMENT:
These procedures are applicable to all flight phases from takeoff to landing. Monitor
the ambient air temperature. While severe icing may form at temperatures as cold as
-18 degrees Celsius, increased vigilance is warranted at temperatures around freezing
with visible moisture present. If the visual cues specified in the Limitations Section of
the AFM for identifying severe icing conditions are observed, accomplish the following:
• Immediately request priority handling from Air Traffic Control to facilitate a route or
an altitude change to exit the severe icing conditions in order to avoid extended
exposure to flight conditions more severe than those for which the aircraft has been
certificated.
• Avoid abrupt and excessive manoeuvring that may exacerbate control difficulties.
• Do not engage the autopilot.
• If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot.
• If an unusual roll response or uncommanded roll control movement is observed,
reduce the angle-of-attack.
• Do not extend flaps when holding in icing conditions. Operation with flaps extended
can result in a reduced wing angle-of-attack, with the possibility of ice forming on the
upper surface further aft on the wing than normal, possibly aft of the protected area.
• If the flaps are extended, do not retract them until the airframe is clear of ice.
• Report these weather conditions to Air Traffic Control.”
Note:
This may be accomplished by inserting a copy of this AD in the AFM or by
incorporating a manufacturer’s flight manual revision that contains the wording per this
AD.
3. Flight Crew Notification
Operators must ensure that flight crew are aware of the flight manual revision.
(FAA AD 98-05-14R1 refers)
Compliance:
By 10 May 1998.
Effective Date:
10 April 1998
DCA/CESS210/30
Severe Icing Conditions - Flight Manual Revision
Applicability:
Model T210R aircraft, all S/N.
Requirement:
To minimise the potential hazards associated with operating the aircraft in severe icing
conditions (by providing more clearly defined procedures and limitations associated
with such conditions), incorporate the following into the Aircraft Flight Manual (AFM):1. Limitations Section of the Aircraft Flight Manual
“WARNING
Severe icing may result from environmental conditions outside of those for which the
aircraft is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions
(supercooled liquid water and ice crystals) may result in ice build-up on protected
surfaces exceeding the capability of the ice protection system, or may result in ice
forming aft of the protected surfaces. This ice may not be shed using the ice
protection systems, and may seriously degrade the performance and controllability of
the aircraft.
Issued 22 October 2015
Page 14 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
•
During flight, severe icing conditions that exceed those for which the aircraft is
certificated shall be determined by the following visual cues. If one or more of these
visual cues exists, immediately request priority handling from Air Traffic Control to
facilitate a route or an altitude change to exit the icing conditions.
Unusually extensive ice accumulation on the airframe and windshield in areas
not normally observed to collect ice.
-
Accumulation of ice on the lower surface of the wing aft of the protected area.
Accumulation of ice on the engine nacelles and propeller spinners farther aft
than normally observed.
•
Since the autopilot, when installed and operating, may mask tactile cues that
indicate adverse changes in handling characteristics, use of the autopilot is prohibited
when any of the visual cues specified above exist, or when unusual lateral trim
requirements or autopilot trim warnings are encountered while the aircraft is in icing
conditions.
•
All wing icing inspection lights must be operative prior to flight into known or
forecast icing conditions at night. This supersedes any relief provided by the Master
Minimum Equipment List (MMEL).”
2. Normal Procedures Section of the Aircraft Flight Manual
“THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE
IN-FLIGHT ICING:
• Visible rain at temperatures below 0 degrees Celsius ambient air temperature.
• Droplets that splash or splatter on impact at temperatures below 0 degrees Celsius
ambient air temperature.
PROCEDURES FOR EXITINGTHE SEVERE ICING ENVIRONMENT:
These procedures are applicable to all flight phases from takeoff to landing. Monitor
the ambient air temperature. While severe icing may form at temperatures as cold as
-18 degrees Celsius, increased vigilance is warranted at temperatures around freezing
with visible moisture present. If the visual cues specified in the Limitations Section of
the AFM for identifying severe icing conditions are observed, accomplish the following:
• Immediately request priority handling from Air Traffic Control to facilitate a route or
an altitude change to exit the severe icing conditions in order to avoid extended
exposure to flight conditions more severe than those for which the aircraft has been
certificated.
• Avoid abrupt and excessive manoeuvring that may exacerbate control difficulties.
• Do not engage the autopilot.
• If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot.
• If an unusual roll response or uncommanded roll control movement is observed,
reduce the angle-of-attack.
• Do not extend flaps when holding in icing conditions. Operation with flaps extended
can result in a reduced wing angle-of-attack, with the possibility of ice forming on the
upper surface further aft on the wing than normal, possibly aft of the protected area.
• If the flaps are extended, do not retract them until the airframe is clear of ice.
• Report these weather conditions to Air Traffic Control.”
Note:
This may be accomplished by inserting a copy of this AD in the AFM or by
incorporating a manufacturer’s flight manual revision that contains the wording per this
AD.
Issued 22 October 2015
Page 15 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
3. Flight Crew Notification
Operators must ensure that flight crew are aware of the flight manual revision.
(FAA AD 98-20-33 refers)
Compliance:
By 23 November 1998
Effective Date:
23 October 1998
DCA/CESS210/31
Fuel Strainer Assembly – Inspection
Applicability:
Models 210E, 210F, 210G, 210H, 210J, 210K/T210K, 210L/T210L, 210M/T210M,
210N/T210N, T210F, T210G, T210H, T210J and P210N series aircraft fitted with
Cessna P/N 0756005-2 top assembly, P/N 0756005-8 fuel strainer assembly, or a P/N
0756005-9 fuel strainer assembly shipped from Cessna between 12 December 1996,
and 5 September 1997.
Note:
All aircraft S/Ns, including those manufactured in France that have a capital "F" or
"FR" prefix on the model number:
Requirement:
To prevent foreign material from entering the fuel system and engine, which could
result in loss of engine power or complete engine stoppage during flight, accomplish
the following:1. Measure the standpipe in the fuel strainer assembly (tube in the filter strainer top
assembly) for a visible maximum length of 1.68 inches, per Cessna SEB 97-9 If the
standpipe measures greater than 1.68 inches, prior to further flight, replace the filter
strainer top assembly per SEB 97-9.
2. Do not fit to any aircraft a fuel strainer assembly where the standpipe measures
greater than 1.68 inches.
(FAA AD 2000-06-01 refers)
Compliance:
1. By 27 April 2001.
2. From 27 April 2000.
Effective Date:
27 April 2000
DCA/CESS210/32
Applicability:
Horizontal Stabiliser Brackets – Inspection and Replacement
Model No:
S/N:
210G
21058819 through to 21058936
210H
21058937 through to 21059061
210J
21059062 through to 21059199
210K and T210K
21059200 through to 21059502
210L and T210L
21059503 through to 21061041, and 21061043 through to
21061573
210M and T210M
21061042, and 21061574 through to 21062954
210N and T210N
21062955 through to 21064897
P210N
P21000001 through to P21000834
T210G
T210-0198 through to T210-0307
T210H
T210-0308 through to T210-0392
T210J
T210-0393 through to T210-0454, and 21058140
Issued 22 October 2015
Page 16 of 26
CAA of NZ
Aeroplanes
Requirement:
Cessna 210 Series
To prevent structural failure of the horizontal stabiliser attachment brackets
accomplish the following;
1. Check the maintenance records to determine whether a horizontal stabiliser
attachment reinforcement bracket, P/N 1232624-1, shipped by Cessna from February
27, 1998, through March 17, 2000, is installed. If, by checking the maintenance
records, the owner/operator can positively show that a horizontal stabiliser attachment
reinforcement bracket, P/N 1232624-1, shipped by Cessna from February 27, 1998,
through March 17, 2000, is not installed, then the inspection requirement of part 2 and
the replacement requirement of part 3 of this AD do not apply. You must make an
entry into the aircraft records that shows compliance with part 1 of this AD
2. Visually inspect the right and left horizontal stabiliser attachment reinforcement
brackets, P/N 1232624-1, for the existence of seam welds along both the lower
inboard and outboard wall/flange. If the right and left horizontal stabiliser attachment
reinforcement bracket has seam welds along both the lower inboard and outboard
wall/flange, no further action is required. Record compliance with part 2 of this AD.
3. If no seam weld is found along both the lower inboard and outboard wall/flange
on the right and left horizontal stabiliser attachment reinforcement bracket during the
inspection required in paragraph (d)(2) of this AD, replace with a new or airworthy P/N
1232624-1 horizontal stabiliser attachment reinforcement bracket.
4.
Do not install any P/N 1232624-1 horizontal stabiliser attachment reinforcement
bracket unless the bracket has passed the inspection requirements of part 2 of this
AD.
(FAA AD 2002-07-01 refers)
Compliance:
Effective Date:
1.
Within 50 hours TIS.
2.
Within 50 hours TIS if applicable.
3.
Before further flight.
4.
After effective date.
26 April 2002
DCA/CESS210/33
Applicability:
Shoulder Harness – Inspection & Modification
Model
210
210-5 (205)
210-5 (205A)
210A
210B
210C
210D
210E
210F
210G
210H
210J
210K
T210F
T210G
T210H
T210J
T210K
Issued 22 October 2015
S/N 618 and 57001 through to 57575,
S/N 641, 648, and 205-0001 through to 205-0480.
S/N 205-0481 through 205-0577,
S/N 616 and 21057576 through to 21057840,
S/N 21057841 through to 21058085,
S/N 21058086 through to 21058139 and,
21058141 through to 21058220,
S/N 21058221 through to 21058510,
S/N 21058511 through to 21058715,
S/N 21058716 through to 21058818,
S/N 21058819 through to 21058936,
S/N 21058937 through to 21059061.
S/N 21059062 through to 21059199,
S/N 21059200 through to 21059351,
S/N T210-0001 through to T210-0197,
S/N T210-0198 through to T210-0307,
S/N T210-0308 through to T210-0392,
S/N T210-0393 through to T210-0454,
S/N 21059200 through to 21059351,
Page 17 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
Embodied with Cessna Mod Kit AK210-77, AK210-93, AK210-171, AK210-172,
AK210-173 or AK210-174.
Requirement:
To prevent slippage of the pilot and copilot shoulder harness, which could result in
serious injury to the pilot and copilot, accomplish the following:
1.
Inspect the upper shoulder harness adjuster P/N 443030-401 for the presence
of a retainer spring, in accordance with Cessna Single Engine Service Bulletin SEB868, Revision 1.
2. If a retainer spring is found during the inspection of the upper shoulder harness
adjuster, prior to further flight remove the spring by cutting each side; and stamp out
the -401 identification number in accordance with Cessna Single Engine Service
Bulletin SEB86-8, Revision 1
3. If a retainer spring is not found during the inspection of the upper shoulder
harness adjuster, make an entry in the airplane log book showing compliance with this
AD.
4. Only incorporate Cessna Accessory Kits that have been inspected and modified
in accordance with this AD.
(FAA AD 2004-19-01 refers)
Compliance:
Within the next 100 hours TIS
Effective Date:
25 November 2004
DCA/CESS210/34
Applicability:
Alternate Static Source Selector – Inspection
The following aircraft fitted with an alternate static air source selector valve P/N
2013142-18 since 19 November 2007:
Model 210 aircraft, all S/N
Model 210–5 (205) aircraft, all S/N
Model T210F aircraft, all S/N
Model T210G aircraft, all S/N
Model T210H aircraft, all S/N
Model T210J aircraft, all S/N
Model T210K aircraft, all S/N
Model T210L aircraft, all S/N
Model T210M aircraft, all S/N
Model T210N aircraft, all S/N
Model T210R aircraft, all S/N
Note 1:
P/N 2013142-18 superseded P/N 2013142-9, -13 and -17.
Requirement:
To prevent erroneous indications from the altimeter, airspeed and vertical speed
indicator which could cause the pilot to react to incorrect flight information and
possibly result loss of aircraft control, accomplish the following:
1. Inspect the alternate static air source selector valve and establish whether the
static air port on the forward end of the valve is clearly visible and not covered by the
P/N identification placard.
Issued 22 October 2015
Page 18 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
If the static air port is found covered by the P/N identification placard, remove the
placard from the selector valve body and ensure the port is open and unobstructed.
Discard the placard and record the P/N of the alternate static air source selector valve
in the aircraft logbook.
Note 2:
If the alternate static air source selector valve port is found covered by the
identification placard, submit a defect report form CA005D to the Civil Aviation and
provide the aircraft model, S/N and aircraft TTIS.
2. Before fitting an alternate static air source selector valve P/N 2013142–18 to any
aircraft, accomplish requirement 1 of this AD.
(FAA AD 2008-10-02 refers)
Compliance:
Effective Date:
1.
Before further flight.
2.
From 12 May 2008.
12 May 2008
DCA/CESS210/35
Alternate Static Source Selector – Inspection
Applicability:
Model 210, 210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L,
210M, 210N, 210R, 210-5 (205), 210-5A (205A), T210F, T210G, T210H, T210J,
T210K, T210L, T210M, T210N and T210R aircraft, all S/N manufactured between 1
January 1993 and 31 March 2008, or fitted with an alternate static air source selector
valve P/N 2013142-18 as a replacement part between 1 January 1993 and 31 March
2008, unless already in compliance with DCA/CESS210/34.
Note 1:
This AD includes aircraft not previously affected by DCA/CESS210/34 and all those
aircraft fitted with an alternate static air source selector valve P/N 2013142-18
between 1 January 1993 and 31 March 2008. Alternate static air source selector valve
P/N 2013142-18 replaced P/N 2013142-9, -13 and -17.
Requirement:
To prevent erroneous indications from the altimeter, airspeed and vertical speed
indicator which could cause the pilot to react to incorrect flight information and
possibly result in loss of aircraft control, accomplish the following:
1. Inspect the alternate static air source selector valve and establish whether the
static air port on the forward end of the valve is clearly visible and not covered by the
P/N identification placard per the procedures in Cessna Single Engine SB SB08-34-02
revision 1 dated 6 October 2008, Cessna Caravan SB CAB08-4 revision 1 dated 6
October 2008, Cessna Single Engine SB SEB08-5 dated 13 October 2008 or Cessna
Multi-engine SB MEB08-6 dated 13 October 2008, as applicable.
If the static air port is found covered by the P/N identification placard, remove the
placard from the selector valve body and ensure the port is open and unobstructed.
Discard the placard and record the P/N of the alternate static air source selector valve
in the aircraft logbook.
2. Before fitting an alternate static air source selector valve P/N 2013142–18 to any
aircraft, accomplish requirement 1 of this AD.
Note 2:
If the alternate static air source selector valve port is found covered by the P/N
identification placard, submit a defect report form CA005D to the Civil Aviation and
provide the aircraft model, S/N and aircraft TTIS.
(FAA AD 2008-26-10 refers)
Compliance:
1. By 3 February 2009 for IFR aircraft, and within the next 100 hours TIS or by 23
May 2009 whichever occurs sooner for non IFR aircraft.
2.
Effective Date:
From 23 January 2009.
23 January 2009
Issued 22 October 2015
Page 19 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
DCA/CESS210/36
Applicability:
Engine Compartment Flexible Hoses – Inspection and Replacement
Model 210D aircraft, S/N 21058221 through to 21058510
Model 210E aircraft, S/N 21058511 through to 21058715
Model T210Faircraft, S/N T210-0001 through to T210-0197
Model 210F aircraft, S/N 21058716 through to 21058818
Model T210G aircraft, S/N T210-0198 through to T210-0307
Model 210G aircraft, S/N 21058819 through to 21058936
Model T210H aircraft, S/N T210-0307 through to T210-0392
Model 210H aircraft, S/N 21058937 through to 21059062
Note 1:
Affected aircraft are fitted with Aeroquip 601 series or Stratoflex 156 series hose
assemblies with Cessna P/N S1236-x-xxxx. These hose assemblies have a steel
braided exterior.
Requirement:
To prevent flammable fluid leaks from the flexible hose assemblies in the engine
compartment, accomplish a visual inspection of the engine compartment flexible
hoses as follows:
For fuel Lines:
Pressurize the fuel lines with the boost pump operating in high position and the
mixture control in the idle cutoff position. With the fuel lines pressurized, inspect all
flexible hoses for signs of fuel stains, wetness and leaks. Allow sufficient time for
excess fuel to drain overboard from the engine manifold before attempting an engine
start.
For Oil Lines:
Inspect all the oil lines for indications of wetness or leaks.
If any defects or leaks are found in any fuel or oil lines, replace defective hoses and
accomplish all corrective actions before further flight.
Note 2:
Cessna Service Letter SE71-7, Supplement No. 1 dated 3 November and later
approved revision pertains to the subject of this AD.
Note 3:
The repetitive inspections required by this AD may be terminated when all affected
hose assemblies are replaced with assemblies which have a Cessna metal tag with a
date. TSO-C53a Type C approved hose assemblies are acceptable replacement
parts. Refer to the manufacturer approved ICA’s for the continued airworthiness
requirements of engine compartment fuel and oil hoses.
(FAA AD 71-24-04 refers)
Compliance:
Within the next 100 hours TIS unless previously accomplished, and thereafter at
intervals not to exceed 100 hours TIS.
Effective Date:
29 July 2010
DCA/CESS210/37
Applicability:
Main Landing Gear Saddles – Inspection and Replacement
Model 210 through to model 210J aircraft, S/N 57001 through 57575, 21057576
through to 21059199
Model T210F through to model T210J aircraft, S/N T210-0001 through to T210-0454.
Requirement:
To prevent possible main landing gear extension failures, accomplish the following:
1.
Issued 22 October 2015
For model 210 and 210A aircraft, S/N 21057001 through to 21057840:
Page 20 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
Inspect P/N 1241004-1 and 1241004-2 landing gear saddles for cracks using dye
penetrant method in accordance with either procedure 1 or 2 as specified in note 4
and 5 of this AD. Pay particular attention to the critical areas shown in Figure 1 of this
AD.
If any cracks are found, replace saddles before further flight.
2.
For model 210 and 210A aircraft, S/N 21057001 through to 21057840:
Replace P/N 1241004-1 and 1241004-2 main landing gear saddles with new parts
with P/N per Cessna Service Letter SE 75-26 dated 5 December or later approved
revisions.
Note 1:
The accomplishment of requirement 2 is a terminating action to the repetitive
inspections mandated by requirement 1 of this AD.
3. For models 210B through to 210G aircraft, S/N 21057841 through to 21058936,
and model T210F and T210G aircraft, S/N T210-0001 through to T210-0307:
Inspect P/N 1241423-1 and 1241423-2 main landing gear saddles for cracks using
dye penetrant method in accordance with either procedure 1 or 2 as specified in note
4 and 5 of this AD. Pay particular attention to the critical areas shown in Figure 2 of
this AD.
If any cracks are found, replace saddles before further flight.
Issued 22 October 2015
Page 21 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
4. For models 210B through to 210G aircraft, S/N 21057841 through to 21058936,
and model T210F and T210G aircraft, S/N T210-0001 through to T210-0307:
Replace P/N 1241423-1 and 1241423-2 main landing gear saddles with improved
saddles of the same P/N per Service Letter SE 75-26.
Note 2:
The accomplishment of requirement 4 is a terminating action to the repetitive
inspections mandated by requirement 3 of this AD.
5. For aircraft fitted with improved main landing gear saddles per Service Letter SE
75-26 and models 210H and 210J aircraft, S/N 21058937 through to 21059199, and
models T210H and T210J aircraft, S/N T210-0308 through to T210-0454:
Inspect the P/N 1241423-1 and 1241423-2 main landing gear saddles for cracks using
dye penetrant method in accordance with either procedure 1 or 2 as specified in note
4 and 5 of this AD. Pay particular attention to the critical areas shown in Figure 2 of
this AD.
If any cracks are found, replace saddles before further flight.
Note 3:
For those aircraft on which the main landing gear saddles have been replaced, the
compliance time of this AD is the TIS of the saddles rather than the TIS of the aircraft.
Note 4:
Procedure 1 - Place the aircraft on jacks and disconnect the main landing gear doors.
Retract the landing gear and perform dye penetrant inspection of the saddle fittings
from underneath the aircraft. Refer to applicable Cessna Maintenance Manual
instructions for disconnecting main landing gear doors.
Note 5:
Procedure 2 - With the aircraft in normal ground attitude, remove the inspection cover
in the floorboard area of the aircraft and perform dye penetrant inspection of the
saddle fittings from inside the aircraft. Refer to applicable Cessna Maintenance
Manual instructions for removal of inspection cover in floorboard area.
Note 6:
Installation of main landing gear saddles P/N 1294151-1 and 1294151-2 in lieu of P/N
1241423-1 and 1241423-2 is an equivalent means of compliance with this AD.
(FAA AD 76-14-07R2 refers)
Compliance:
1.
For aircraft with 1000 hours or more TTIS:
Within the next 25 hours TIS, and thereafter at intervals not to exceed 25 hours TIS.
For aircraft with less than 1000 hours TTIS:
Before accumulation of 1025 hours TTIS, and thereafter at intervals not to exceed 25
hours TIS.
2.
Within the next 100 hours TIS unless previously accomplished, and thereafter at
intervals not to exceed 1000 hours TIS.
3.
For aircraft with 1000 hours or more TTIS:
Within the next 25 hours TIS, and thereafter at intervals not to exceed 25 hours TIS.
For aircraft with less than 1000 hours TTIS:
Before accumulation of 1025 hours TTIS, and thereafter at intervals not to exceed 25
hours TIS.
4.
Within the next 100 hours TIS.
5.
For aircraft with more than 1200 hours TTIS:
Within the next 100 hours TIS, and thereafter at every annual inspection.
Issued 22 October 2015
Page 22 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
For aircraft with 1200 hours or less TTIS:
Before accumulation of 1300 hours TTIS, and thereafter at every annual inspection.
Effective Date:
29 July 2010
DCA/CESS210/38
Applicability:
Fuel Quantity System – Inspection and Rework
Model 210G, 210H and 210J aircraft, S/N 21058819 through to 21059199
Model 210M and 210N aircraft, S/N 21062274 through to 21063025
Model T210G, T210H and T210J aircraft, S/N T210-0198 through to T210-0454 and
21058140
Model T210M and T210N aircraft, S/N 21062274 through to 21063025
Model P210N aircraft, S/N P21000001 through to P21000141.
Requirement:
To prevent possible binding of fuel quantity transmitter float arms which could result in
a false fuel quantity indication, accomplish the following:
1. For model 210M, 210N, T210M and T210N aircraft, S/N 21062761 through to
21063025 and model P210N aircraft, S/N P21000063 through to P21000141:
Completely fill the left and right fuel tanks and drain the tanks with the engine
inoperative and the aircraft stationary in the level ground attitude. Observe the fuel
quantity gauge during draining and once all the fuel is drained determine if the
respective fuel quantity gauge indicates empty. Remove any Cessna P/N C6680020101 or -0102 fuel quantity transmitter which indicates an erroneous fuel quantity
reading and inspect for binding of the float arm. If a binding float arm is found replace
with an airworthy part before further flight. After replacement, inspect for fuel leaks
and determine correct operation of the fuel gauging system.
2. For models 210G, 210H, 210J and 210M aircraft, S/N 21058819 through to
21059199 and 21062274 through to 21062760, model T210G, T210H, T210J and
T210M aircraft, S/N T210-0198 through to T210-0454, 21058140 and 21062274
through to 21062760 and model P210N aircraft, S/N P21000001 through to
P21000062:
Review the aircraft maintenance records and determine if a fuel quantity transmitter
has been replaced since 7 June 1978. If a fuel quantity transmitter has not been
replaced since 7 June 1978 make an entry in the aircraft maintenance records
indicating that this AD has been accomplished and the aircraft can be returned to
service. And if a fuel quantity transmitter has been replaced since 7 June 1978,
comply with requirement 1 of this AD.
Note 1:
The review the aircraft maintenance records may be performed and certified under
the provision in Part 43 Appendix A.1 (7) by the holder of a current pilot licence, if that
person is rated on the aircraft, appropriately trained and authorised (Part 43, Subpart
B refers), and the maintenance is recorded and certified as required by Part 43.
Note 2:
Cessna Service Letter SE 78-69, dated 15 November 1978 or later approved
revisions pertains to the subject of this AD.
(FAA AD 78-26-12 refers)
Compliance:
Effective Date:
1.
Before further flight unless previously accomplished.
2.
Before further flight unless previously accomplished.
29 July 2010
Issued 22 October 2015
Page 23 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
DCA/CESS210/39
Applicability:
Throttle and Mixture Controls – Inspection and Modification
Model 210B, 210C, 210D, 210E, 210F, 210G, 210H and 210J aircraft, S/N 21057841
through to 21059199
Model T210F, T210G, T210H and T210J aircraft, S/N T210-O001 through to T2100454).
Requirement:
To reduce the possibility of engine control failure and loss of engine power control,
accomplish the following:
Accomplish a visual inspection of the ends of the engine throttle and mixture control
cables to determine if the sleeve and bushing are secured by a drive screw. If so,
inspect, modify and/or replace engine throttle and mixture controls per the instructions
in Cessna Single-Engine Service Letter SE69-16 dated 22 July 1969 or later approved
revisions.
(FAA AD 85-03-01 refers)
Compliance:
Within the next 100 hours TIS unless previously accomplished.
Effective Date:
29 July 2010
DCA/CESS210/40
Applicability:
Engine Controls – Inspection and Rework
Model 210C through to 210M and model T210K through to T210M aircraft, S/N
21058086 through to 21062954, and
Model T210F through to T210J aircraft, S/N T210-0001 through T210-0454, and
Model P210N aircraft, S/N P21000001 through to P21000150,
Manufactured up to model year 1978 and fitted with ball type rod ends on the engine
controls.
Requirement:
To prevent loss of engine power due to possible loss of attachment of the engine
controls, accomplish the following:
Modify the engine controls installation by installing a drilled steel bolt, AN3l0 type
castellated nut and a steel cotter pin per the instructions in Cessna Single-Engine
Customer Care Service Information Letter SE79-6 or later approved revisions.
(FAA AD 86-24-07 refers)
Compliance:
Within the next 100 hours TIS unless previously accomplished.
Effective Date:
29 July 2010
DCA/CESS210/41
Seat Adjustment Mechanism – Inspection and Replacement
Applicability:
Model 210, 210-5 (205), 210-5A (205A), 210A, 210B, 210C, 210D, 210E, 210F, 210G,
210H, 210J, 210K, 210L, 210M, 210N, 210R, P210N, P210R, T210F, T210G, T210H,
T210J, T210K, T210L, T210M, T210N and T210R aircraft, all S/N.
Note 1:
This AD supersedes DCA/CESS210/20A to introduce additional inspection
requirements, to improve the clarity of the required inspections, and provide improved
figures/graphics. The FAA continue to receive reports of inadvertent seat movement.
These reports included an incident of a seat separating from the seat track due to
wear of the seat roller housing tangs.
Issued 22 October 2015
Page 24 of 26
CAA of NZ
Aeroplanes
Requirement:
Cessna 210 Series
To prevent seat slippage or disengagement of the seat roller housing from the seat
rail which could result in the pilot/copilot being unable to reach all the controls and loss
of aircraft control, accomplish the following:
Accomplish the inspections and corrective actions in FAA AD 2011-10-09 on the seat
rails; seat rollers, washers, and axle bolts or bushings; seat roller housings and the
tangs; and the lock pin springs.
Note 2:
A copy of FAA AD 2011-10-09 can be obtained from the FAA website at:
http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgAD.nsf/MainFrame?OpenFram
eSet
(FAA AD 2011-10-09 refers)
Compliance:
Within the next 100 hours TIS after the last inspection accomplished per
DCA/CESS210/20A (FAA AD 87-20-03 R2 refers) or by 30 June 2012 whichever
occurs sooner, and thereafter at intervals not to exceed 100 hours TIS or every 12
months whichever occurs sooner.
Effective Date:
30 June 2011
DCA/CESS210/42
Main Spars – Inspection and Replacement
Applicability:
Model 210 series, P210 series and T210 series aircraft listed in the applicability
section of FAA AD 2012-10-04.
Note 1:
This AD requires an inspection of the wing main spar lower caps for cracks. If any
cracks are found then affected parts must be replaced or an approved modification
must be embodied.
Requirement:
To prevent failure of the wing main spar lower caps due to possible cracks,
accomplish the inspections and corrective actions specified in FAA AD 2012-10-04.
Note 2:
A copy of FAA AD 2012-10-04 can be obtained from the FAA AD website at
http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgAD.nsf/MainFrame?OpenFram
eSet
(FAA AD 2012-10-04 refers)
Compliance:
At the compliance times specified in FAA AD 2012-10-04.
Effective Date:
5 June 2012
Issued 22 October 2015
Page 25 of 26
CAA of NZ
Aeroplanes
Cessna 210 Series
From 1 October 2012 the Civil Aviation Authority of New Zealand (CAA) will no longer rewrite the
text of State of Design ADs. Applicable State of Design ADs will be listed below and can be
obtained directly from the National Airworthiness Authority (NAA) web site. The link to the NAA
web site is available on the CAA web site at
http://www.caa.govt.nz/Airworthiness_Directives/states_of_design.html
If additional NZ ADs need to be issued when an unsafe condition is found to exist in an aircraft or
aeronautical product in NZ they will be added to the list below.
72-07-09
Effective Date:
Cancelled – DCA/CESS210/43 refers
18 June 2015
* DCA/CESS210/43B
Applicability:
Vertical Stabiliser – Inspection
Cessna 205 series aircraft, all S/N.
Cessna 210 series aircraft, S/N 21057841 through to 21059739.
Cessna T210 series aircraft, S/N T210-0001 through to T210-0454, and 21059200
through to 21059739.
Note 1:
DCA/CESS210/43B revised to clarify the requirement.
Requirement:
For aircraft not embodied with an improved aft tailcone bulkhead installation per
Cessna Single Engine Service Bulletin SEB99-12 original issue, dated 13 September
1999, or later FAA approved revisions:
Inspect the aft fin spar attachment bolts, the forward and aft vertical fin attachment
structure per the requirements in FAA AD 72-07-09.
Accomplish corrective actions as required, before further flight, per FAA AD 72-07-09.
Note 2:
Cessna Service Letter SE72-3 dated 11 February 1972 pertains to the subject of this
AD.
Note 3:
For aircraft embodied with the modification specified in SEB99-12, the repetitive
inspections/corrective actions specified in the Cessna Maintenance Manual are
applicable. SEB99-12 introduces an improved vertical stabiliser aft spar attachment
bulkhead which is approved as a terminating action to the repetitive inspections
mandated by FAA AD 72-07-09.
(FAA AD 72-07-09 refers)
Compliance:
At 1000 hours TTIS after 17 October 1974 (the effective date of FAA AD 72-07-09),
and thereafter at intervals not to exceed 100 hours TIS.
Effective Date:
DCA/CESS210/43 - 18 June 2015
DCA/CESS210/43A - 30 July 2015
DCA/CESS210/43B - 22 October 2015
Issued 22 October 2015
Page 26 of 26
CAA of NZ
Was this manual useful for you? yes no
Thank you for your participation!

* Your assessment is very important for improving the work of artificial intelligence, which forms the content of this project

Download PDF

advertisement