Document ID: FAA-2010-1101-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Cessna Aircraft Co. Models 150, 152, 170, 172, 175, 177, 180, 182, 185, 188, 190, 195, 206, 207, 210, T303, 336, and 337 Airplanes
Posted Date: 2010-11-08T05:00Z

[Federal Register Volume 75, Number 215 (Monday, November 8, 2010)]
[Proposed Rules]
[Pages 68543-68548]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-28158]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1101; Directorate Identifier 2009-CE-013-AD]
RIN 2120-AA64

Airworthiness Directives; Cessna Aircraft Company Models 150, 
152, 170, 172, 175, 177, 180, 182, 185, 188, 190, 195, 206, 207, 210, 
T303, 336, and 337 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 87-20-03 
R2, which applies to certain Cessna Aircraft Company (Cessna) 150, 152, 
170, 172, 175, 177, 180, 182, 185, 188, 190, 195, 206, 207, 210, T303, 
336, and 337 series airplanes. AD 87-20-03 R2 currently requires 
repetitive inspections and replacement of parts, if necessary, of the 
seat rail and seat rail holes; seat pin engagement; seat rollers, 
washers, and axle bolts or bushings; wall thickness of roller housing 
and the tang; and lock pin springs. Since we issued AD 87-20-03 R2, we 
have added steps to the inspection procedures, added revised figures, 
and clarified some of the existing steps. Consequently, this proposed 
AD would retain all of the actions from the previous AD and add steps 
to the inspection procedures in the previous AD. We are proposing this 
AD to prevent seat slippage or the seat roller housing from departing 
the seat rail, which may consequently cause the pilot/copilot to be 
unable to reach all the controls. This failure could lead to

[[Page 68544]]

the pilot/copilot losing control of the airplane.

DATES: We must receive comments on this proposed AD by December 23, 
2010.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, ACE-
118W, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, 
Room 100, Wichita, Kansas 67209; telephone: (316) 946-4123; fax: (316) 
946-4107.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2010-1101; Directorate Identifier 2009-CE-013-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    Reports of seats slipping on the rails on Cessna airplanes caused 
us to issue AD 87-20-03 R2, Amendment 39-6669. AD 87-20-03 R2 currently 
requires repetitive inspections and replacement of parts if necessary 
of the seat rail and seat rail holes; seat pin engagement; seat 
rollers, washers, and axle bolts or bushings; wall thickness of roller 
housing and the tang; and lock pin springs on Cessna 150, 152, 170, 
172, 175, 177, 180, 182, 185, 188, 190, 195, 206, 207, 210, T303, 336, 
and 337 series airplanes.
    We have in the last 20 years received several reports of accidents, 
some fatal, for Cessna airplanes where the primary latch pin for the 
pilot/copilot seat is not properly engaged in the seat rail/track. 
There have also been incidents where the seat roller housing has 
departed the seat rail. Consequently, we have added steps to the 
inspection procedures, added revised figures, and clarified some of the 
existing steps.
    This condition, if not corrected, could result in seat slippage or 
the seat roller housing departing from the seat rail, which may 
consequently cause the pilot/copilot to be unable to reach all the 
controls. This failure could lead to the pilot/copilot losing control 
of the airplane.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This proposed AD 
would supersede AD 87-20-03 R2 with a new AD that would retain all of 
the actions from the previous AD and add steps to the inspection 
procedures in the previous AD.

Costs of Compliance

    We estimate that this proposed AD would affect 36,000 airplanes in 
the U.S. registry.
    The estimated total cost on U.S. operators includes the cumulative 
costs associated with AD 87-20-03 R2. The required actions of this 
proposed AD are the same as in AD 87-20-03 R2 with the exception of 
some added steps to the inspection, which do not increase work-hours. 
The increased estimated cost of this AD is due to increased labor cost 
and parts cost from 1987 when AD 87-20-03 R2 was issued.
    We estimate the following costs to do the proposed inspections:

----------------------------------------------------------------------------------------------------------------
                                                                                 Total cost per   Total cost on
                  Labor cost                              Parts cost                airplane      U.S. operators
----------------------------------------------------------------------------------------------------------------
1 work-hour x $85 per hour = $85..............  Not applicable................             $85       $3,060,000
----------------------------------------------------------------------------------------------------------------

     We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of airplanes that may need 
this replacement:

------------------------------------------------------------------------
                                                          Total cost per
             Labor cost                   Parts cost         airplane
------------------------------------------------------------------------
Seat rail: 2 work-hours x $85 per    $225 per rail......            $395
 hour = $170 per rail.
Seat roller kit: 2 work-hours per    110................             280
 seat (less per leg) x $85 per hour
 = $170.
Miscellaneous parts, such as seat    15.................             100
 rollers, washers, bushings, bolts,
 lock pin springs, etc.: 1 work-
 hour per seat x $85 per hour = $85.
------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

[[Page 68545]]

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at http://www.regulations.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5527) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Airworthiness Directive 
(AD) 87-20-03 R2, Amendment 39-6669, and adding the following new AD:

Cessna Aircraft Company: Docket No. FAA-2010-1101; Directorate 
Identifier 2009-CE-013-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by December 23, 2010.

Affected ADs

    (b) This AD supersedes AD 87-20-03 R2, Amendment 39-6669.

Applicability

    (c) This AD applies to all serial numbers of the following 
Cessna Aircraft Company (Cessna) Models that are certificated in any 
category:

------------------------------------------------------------------------
                                 Models
-------------------------------------------------------------------------
150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, 150M,
 A150K, A150L, A150M, F150F, F150G, F150H, F150J, F150K, F150L, F150M,
 FA150K, FA150L, FA150M, FRA150L, and FRA150M
152, A152, F152, and FA152
170, 170A, and 170B
172, 172A, 172B, 172C, 172D, 172E, 172F (USAF T-41A), 172G, 172H (USAF T-
 41A), 172I, 172K, 172L, 172M, 172N, 172P, 172Q, 172RG, F172D, F172E,
 F172F, F172G, F172H, F172K, F172L, F172M, F172N, F172P, FR172E, FR172F,
 FR172G, FR172H, FR172J, FR172K, P172D, R172E (USAF T[dash]41B) (USAF T-
 41C and D), R172F (USAF T-41D), R172G (USAF T-41C or D), R172H (USAF T-
 41D), R172J, and R172K
175, 175A, 175B, and 175C
177, 177A, 177B, 177RG, and F177RG
180, 180A, 180B, 180C, 180D, 180E, 180F, 180G, 180H, 180J, and 180K
182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L,
 182M, 182N, 182P, 182Q, 182R, F182P, F182Q, FR182, R182, T182, and
 TR182
185, 185A, 185B, 185C, 185D, 185E, A185E, and A185F
188, 188A, A188, A188A, 188B, A188B, and T188C
190
195, 195A, and 195B
206, P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C,
 TP206D, TP206E, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G,
 U206, U206A,U206B, U206C, U206D, U206E, U206F, and U206G
207, 207A, T207, and T207A
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
T303
336
337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H, F337E, F337F,
 F337G, F337H, FT337E, FT337F, FT337GP, FT337HP, M337B, P337H, T337B,
 T337C, T337D, T337E, T337F, T337G, T337H, and T337H-SP
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports of seats slipping on the rails 
where the primary latch pin for the pilot/copilot seat is not 
properly engaged in the seat rail/track and reports of the seat 
roller housing departing the seat rail. We are issuing this AD to 
prevent seat slippage or the seat roller housing from departing the 
seat rail, which may consequently cause the pilot/copilot to be 
unable to reach all the controls. This failure could lead to the 
pilot/copilot losing control of the airplane.

Compliance

    (e) For all airplanes, to address the unsafe condition described 
in paragraph (d) of this AD, you must do the following actions on 
the seat rails; seat rollers, washers, and axle bolts or bushings; 
seat roller housings and the tangs; and lock pin springs, unless 
already done, initially within the next 100 hours time-in-service 
(TIS) after the last inspection done following AD 87-20-03 R2 or 
within the next 12 calendar months after the effective date of this 
AD, whichever occurs first. Repetitively thereafter do the actions 
at intervals not to exceed every 100 hours TIS or every 12 months, 
whichever occurs first:
    (1) Visually inspect the pilot and copilot seat rails for dirt 
and debris that may prevent engagement of the seat locking pins. 
Before further flight, after any inspection where dirt or debris is 
found, remove the dirt or debris found.
    (2) Lift up the forward edge of each seat to eliminate vertical 
play of the seat locking pin

[[Page 68546]]

in the engagement hole, and from this position, inspect the depth of 
engagement of each seat locking pin (see figure 2). If the rail is 
worn, this depth is measured from the worn surface, not the 
manufactured surface.
    (i) If engagement of any of the seat locking pins measures less 
than 0.15 of an inch, before further flight, replace or repair any 
seat components necessary to achieve a seat pin engagement of a 
minimum of 0.15 of an inch.
    (ii) Repair or replacement of necessary seat components does not 
terminate the repetitive actions required in paragraph (e) of this 
AD.
    (3) Remove the seat from the seat rail.
    (i) Remove the seat stops.
    (ii) Disengage seat belt/shoulder harness from the seat, if 
necessary.
    (iii) Raise vertical adjusting seats to maximum height.
    (iv) Hold seat latches disengaged and slide the seat forward and 
aft to disengage rollers.
    (v) Lift the seat out of the airplane.
    (4) Inspect the diameter of each seat locking pin engagement 
hole in the pilot and copilot seat rails for excessive wear. Due to 
wear on the rail surface at the hole opening, we allow this 
measurement 0.020 of an inch below the surface of the rail. You must 
take this measurement somewhere between the surface of the rail or 
no more than 0.020 of an inch below the surface of the rail.
    (i) If the diameter of any of the holes is 0.42 of an inch or 
more (see figure 1), before further flight, replace the rail.
    (ii) Rail replacement does not terminate the repetitive actions 
required in paragraph (e) of this AD.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TP08NO10.039

[GRAPHIC] [TIFF OMITTED] TP08NO10.040

    (5) Visually inspect the seat rollers for flat spots and inspect 
the rollers and washers for binding. Assure all rollers and washers, 
which are meant to rotate, turn freely on their axles (or bushings 
if installed).
    (i) Before further flight, replace any rollers with flat spots 
and any worn washers.
    (ii) Before further flight, remove and clean the parts if there 
is any binding between the bores of the rollers, washers, or axles.
    (iii) Do not lubricate the rollers, washers, or axles because 
the lubricant will attract dust and other particles that may cause 
binding.
    (6) Inspect the thickness of the tang (see figure 2 and figure 
3). Due to wear of the tang chafing against the seat rail, measure 
the tang thickness where the tang inner edges contact the seat rail.
    (i) If the tang thickness measures less than 0.05 of an inch, 
before further flight replace the roller housing.
    (ii) Replacement of the roller housing does not terminate the 
repetitive actions required in paragraph (e) of this AD.

[[Page 68547]]

[GRAPHIC] [TIFF OMITTED] TP08NO10.041

    (7) Inspect the inner edges of the tangs. Due to wear or 
deformation of the tangs, measure the distance from one tang inner 
edge to the other tang inner edge (see figure 4).
    (i) The maximum distance allowed between tang edges is 0.44 
inches. If the distance between tang inner edges measures 0.44 of an 
inch or more, before further flight, replace the roller housing.
[GRAPHIC] [TIFF OMITTED] TP08NO10.042

    (ii) The minimum measurement allowed for the remaining tang is 
0.130 inches remaining on either of the tangs, from the inner edge 
of the tang to the bend of the roller housing. If the measurement is 
less than 0.130 inches on either of the tangs, before further 
flight, replace the roller housing.
    (iii) Replacement of the roller housing does not terminate the 
repetitive actions required in paragraph (e) of this AD.
    (8) Inspect the springs that keep the lock pins in position in 
the rail holes for positive engagement action. Before further 
flight, replace any spring that does not provide positive 
engagement.
    (9) Visually inspect the seat rails for cracks.
    (i) If there are seat rail cracks that exceed the crack criteria 
in figure 5, before further flight, replace the seat rail.
    (ii) Replacement of the seat rail does not terminate the 
repetitive actions required in paragraph (e) of this AD.
BILLING CODE 4910-13-P

[[Page 68548]]

[GRAPHIC] [TIFF OMITTED] TP08NO10.043

    (10) Reinstall the seat on the seat rail.
    (i) Lift the seat into the airplane and place on the seat rail.
    (ii) Hold seat latch disengaged and slide the seat aft and then 
forward to re-engage rollers.
    (iii) Lower vertical adjusting seats to a comfortable height.
    (iv) Reattach seat belt/shoulder harness to the seat, if 
previously attached to the seat.
    (v) Reinstall the seat stops.

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
ATTN: Gary Park, Aerospace Engineer, ACE-118W, Wichita Aircraft 
Certification Office (ACO), 1801 Airport Road, Room 100, Wichita, 
Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-4107. Before 
using any approved AMOC on any airplane to which the AMOC applies, 
notify your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO.
    (h) AMOCs approved for AD 87-20-03 R2 are approved for this AD.

Related Information

    (i) To view the AD docket, go to U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or 
on the Internet at http://www.regulations.gov.

    Issued in Kansas City, Missouri on November 1, 2010.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-28158 Filed 11-5-10; 8:45 am]
BILLING CODE 4910-13-C