Airworthiness Directives: Cessna Aircraft Company 210, P210, and T210 Series Airplanes

DEPARTMENT OF TRANSPORTATION

14 CFR Part 39

[Docket No. 93-CE-33-AD; Amendment 39-8936; AD 94-12-08]

Airworthiness Directives: Cessna Aircraft Company 210, P210, and

T210 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 92-26-

04, which applies to certain Cessna Aircraft Company (Cessna) 210,

P210, and T210 series airplanes. That AD requires operational checks of

the fuel gauges, fuel cap and adapter modifications, and preflight fuel

system quantity checks. The Federal Aviation Administration (FAA)

received a petition for reconsideration of AD 92-26-04, and

subsequently suspended the effectiveness of this AD while the concerns

specified in the petition were evaluated. This action retains certain

requirements of AD 92-26-04, and incorporates certain items raised by

the petition for reconsideration. The actions specified by this AD are

intended to prevent loss of engine power caused by inadvertent fuel

loss or inadequate fuel servicing.

DATES: Effective July 22, 1994.

The incorporation by reference of certain publications listed in

the regulations was previously approved by the Director of the Federal

Register as of January 22, 1993.

ADDRESSES: Service information that applies to this AD may be obtained

from the Cessna Aircraft Company, Customer Services, P.O. Box 1521,

Wichita, Kansas 67201. This information may also be examined at the

FAA, Central Region, Office of the Assistant Chief Counsel, room 1558,

601 E. 12th Street, Kansas City, Missouri 64106; or at the Office of

the Federal Register, 800 North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Paul O. Pendleton, Aerospace

Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport

Road, room 100, Wichita, Kansas 67209; telephone (316) 946-4143;

facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to include an AD that would apply

to certain Cessna 210, P210, and T210 series airplanes was published in

the Federal Register on August 24, 1993 (58 FR 44621). The action

proposed to supersede AD 92-26-04, Amendment 39-8431 (57 FR 57658,

December 7, 1992), with a new AD that would require the following on

Cessna 210, P210, and T210 series airplanes:

Retain the fuel gauge operational checks, fuel cap and

adapter modifications, and preflight fuel system quantity checks

currently required by AD 92-26-04;

Provide the option of utilizing approved alternative

procedures for calibrating the fuel systems;

Provide the option of accomplishing fuel capacity

checks after refueling the airplane or installing raised fuel caps;

and

Revise the applicability of the actual AD to more fully

clarify which airplanes are affected.

Interested persons have been afforded an opportunity to participate

in the making of this amendment. Due consideration has been given to

the comments received.

Several commenters state that the calibration procedures proposed

are ineffective, very expensive, and the equipment necessary to

accomplish the calibration is unavailable. Two of these commenters

referenced calibration and gauge accuracy procedures that they felt

were more realistic (more effective, less expensive, and available)

than those specified in the proposal. The FAA (1) reviewed the

procedures submitted by the commenters; (2) determined that the

referenced procedures are, at least, as realistic as those proposed;

and (3) incorporated the procedures into the AD.

One commenter recommends limiting the number of hours of operation

before an airplane equipped with uncalibrated fuel gauges must refuel.

The commenter states that this would reduce the cost associated with

requiring accurate fuel gauge calibration. The FAA concurs and has

added this provision to the AD.

Several commenters suggest increasing the pilots' knowledge of the

fuel system limitations through training and advisories. The FAA

concurs that this step is essential for aviation safety; however, AD's

are utilized to correct an unsafe condition that exists or is likely to

develop in aircraft of the same type design. Appropriate fuel system

placarding (specified in the proposed AD) does provide an advisory to

the limitations of the originally certificated fuel system, which could

help increase pilot knowledge. Any other action related to increasing

the pilot's knowledge of fuel system limitations is outside the scope

of AD action. The AD is unchanged as a result of this comment.

One commenter recommends that the FAA not require replacement of

the flush fuel caps because the existing fuel caps are acceptable if

they are properly maintained. The FAA concurs. The proposal included

the option of installing these raised fuel caps or fabricating and

installing a fuel capacity check placard on each wing fuel filler

opening. The AD is unchanged as a result of this comment.

One commenter recommends requiring replacement of the fuel caps

with caps that are not susceptible to fuel leakage or siphoning and

where certificated fuel capacity is easily obtainable. This commenter

states that service experience indicates that the fuel caps originally

certificated on these Cessna 210 series airplanes make fuel servicing

difficult and susceptible to water leakage into the tanks and fuel

siphoning during flight. The FAA does not concur that mandatory fuel

cap replacement is necessary. The FAA has determined that the

accomplishment of certain preflight requirements will provide the same

level of safety as fuel cap replacement. The FAA encourages fuel cap

replacement and the preflight requirements are reduced when replacement

is accomplished. The AD is unchanged as a result of this comment.

After careful review of all available information including the

comments noted above, the FAA has determined that air safety and the

public interest require the adoption of the rule as proposed except for

the incorporation of the calibration and gauge accuracy procedures

referenced above and minor editorial corrections. The FAA has

determined that these procedures and minor corrections will not change

the meaning of the AD nor add any additional burden upon the public

than was already proposed.

The FAA estimates that 5,000 airplanes in the U.S. registry will be

affected by this AD, that it will take approximately 4 workhours per

airplane to accomplish the required action, and that the average labor

rate is approximately $55 an hour. Parts cost approximately $150 per

airplane. Based on these figures, the total cost impact of the AD on

U.S. operators is estimated to be $1,850,000. This figure is based on

the assumption that no affected airplane owner/operator has

accomplished the required action.

In addition, AD 92-26-04 currently has a cost impact of $2,125,000

(5 workhours x $55 per hour plus $150 for parts x 5,000 airplanes)

if the FAA had not suspended the effectiveness of that AD. The cost of

this AD is actually a reduction of one workhour per airplane over that

specified in AD 92-26-04, or a reduction of $275,000 for the entire

U.S. fleet.

The regulations adopted herein will not have substantial direct

effects 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. Therefore, in

accordance with Executive Order 12612, it is determined that this final

rule does not have sufficient federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action: (1) Is

not a ``significant regulatory action'' under Executive Order 12866;

(2) is not a ``significant rule'' under 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. A copy of the final evaluation prepared for this

action is contained in the Rules Docket. A copy of it may be obtained

by contacting the Rules Docket at the location provided under the

caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by

reference, Safety.

Adoption of the Amendment

Accordingly, pursuant to the authority delegated to me by the

Administrator, the Federal Aviation Administration amends part 39 of

the Federal Aviation Regulations (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. App. 1354(a), 1421 and 1423; 49 U.S.C.

106(g); and 14 CFR 11.89.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by removing AD 92-26-04, Amendment 39-

8431 (57 FR 57658, December 7, 1992), and by adding a new airworthiness

directive to read as follows:

94-12-08 Cessna Aircraft Company: Amendment 39-8936; Docket No. 93-

CE-33-AD. Supersedes AD 92-26-04, Amendment 39-8431.

Applicability: The following model and serial number airplanes,

certificated in any category.

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Model Serial No.

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210G through 210R, and. 21058819 through 21065009, and

T210G through T210R.... T210-0198 through T210-0454.

P210N, and P210R....... P21000001 through P21000874.

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Compliance: Required within the next 12 calendar months after

the effective date of this AD, unless already accomplished.

To prevent loss of engine power caused by inadvertent fuel loss

or inadequate fuel servicing, accomplish the following:

(a) Incorporate the Pilot Operating Procedures--Preflight Fuel

System Quantity Check that is Figure 1 of this AD into the airplane

flight manual or airplane records.

Figure 1

Pilot Operating Procedures--Preflight Fuel System Quantity Check

The following procedures are to be used on certain Cessna 210,

P210, and T210 Series airplanes whenever more than 75 gallons of

fuel are needed for range and reserve.

1. Verify that the airplane is level laterally and is

approximately 4.5 degrees nose up (normal nose strut on a level

surface).

Note: The airplane turn and bank instrument may be used to check

lateral leveling.

2. Visually inspect each fuel tank for fuel level with the upper

wing surface when full fuel capacity is intended to be in each tank.

3. Check each fuel cap and seal for security and wing surface

for a lack of fuel stains aft of each fuel cap.

Note: It is highly recommended that the wing tips and flap

trailing edges are checked during flight for evidence of fuel

siphoning.

(b) The incorporation of Figure 1 of this AD into the airplane

flight manual or airplane records as required by paragraph (a) of

this AD may be performed by the owner/operator holding at least a

private pilot certificate as authorized by Sec. 43.7 of the Federal

Aviation Regulations (14 CFR 43.7), and must be entered into the

aircraft records showing compliance with this AD in accordance with

Sec. 43.11 of the Federal Aviation Regulations (14 CFR 43.11).

(c) Calibrate the fuel quantity indicating system at the

unusable (empty) fuel gauge indication by accomplishing either

(c)(1) or (c)(2) of this AD as follows:

(1) Checking (one-time) the fuel gauge calibration by:

(i) Draining the wing fuel tank sumps (defuel the airplane).

(ii) Turning the master switch on, ensuring that the fuel gauges

indicate empty (``E''); and

(iii) Adjusting or replacing the transmitter or gauge, as

required to obtain proper ``empty'' indication with empty wing fuel

tanks; or

(2) Fabricate a \1/8\-inch wide (\1/4\-inch long minimum) red

``Empty'' radial line and center on the gauge glass where the gauge

pointer indicates when the tank is empty; and fabricate and install

adjacent to the fuel gauges a placard (using letters at least \1/8\-

inch in height) with the following words:

Fuel Gauges Not Calibrated, Base All Fuel Calculations on Visual

Inspection, Time and Consumption Figures. With Full Tanks, Maximum

Endurance Is 4 Hours for Flight Planning.

(d) Accomplish either (d)(1) or (d)(2) of this AD as follows:

(1) Install raised fuel caps in accordance with the instructions

to Cessna Service Kit SK210-136, which is referenced by Cessna

Service Bulletin SEB91-10, dated October 25, 1991; or Supplemental

Type Certificate SA2456CE (owned by Mr. William J. Barton) for

Monarch Air & Development, Inc., Assembly No. WW-100-2 fuel caps

(only); or

(2) Fabricate two placards with the following words on each

using letters at least \1/8\-inch in height and install a placard on

each wing fuel filler opening: ``To Assure Full Capacity While

Filling, Fill Slowly During Last 5 Gallons. Recheck For Full After 2

Minutes.''

(e) Special flight permits may be issued in accordance with

Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to a location where the

requirements of this AD can be accomplished.

(f) An alternative method of compliance or adjustment of the

compliance time that provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft Certification Office

(ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita,

Kansas 67209. The request shall be forwarded through an appropriate

FAA Maintenance Inspector, who may add comments and then send it to

the Manager, Wichita ACO.

Note: Information concerning the existence of approved

alternative methods of compliance with this AD, if any, may be

obtained from the Wichita ACO.

(g) The replacement required by this AD shall be done in

accordance with Cessna Service Kit SK210-136, which is referenced by

Cessna Service Bulletin SEB91-10, dated October 25, 1991. This

incorporation by reference was previously approved by the Director

of the Federal Register as of January 23, 1993, in accordance with 5

U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Cessna

Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277. Copies may

be inspected at the FAA, Central Region, Office of the Assistant

Chief Counsel, room 1558, 601 E. 12th Street, Kansas City, Missouri,

or at the Office of the Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(h) This amendment (39-8936) supersedes AD 92-26-04, Amendment

39-8431.

(i) This amendment (39-8936) becomes effective on July 22, 1994.

Issued in Kansas City, Missouri, on June 1, 1994.

Barry D. Clements,

Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 94-13850 Filed 6-7-94; 8:45 am]

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