Airworthiness Directives; Cessna Model 750 Airplanes

[Federal Register Volume 66, Number 69 (Tuesday, April 10, 2001)]
[Rules and Regulations]
[Pages 18521-18523]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-8611]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-63-AD; Amendment 39-12169; AD 2001-07-04]
RIN 2120-AA64


Airworthiness Directives; Cessna Model 750 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Cessna Model 750 airplanes, that requires removal 
of a certain existing bulkhead web doubler, installation of left and 
right bulkhead web doublers, and enlargement of the lightening holes. 
This action is necessary to prevent jamming of the roll control system, 
due to inadequate clearance between the control cable and the web, 
which could result in reduced controllability of the airplane.

DATES: Effective May 15, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 15, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 
67277. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita 
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Shane Bertish, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4156; fax (316) 
946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to

[[Page 18522]]

include an airworthiness directive (AD) that is applicable to certain 
Cessna Model 750 airplanes was published in the Federal Register on 
August 8, 2000 (65 FR 48401). That action proposed to require removing 
a certain existing bulkhead web doubler, installing new left and right 
bulkhead web doublers, and enlarging the lightening holes.

Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

Request To Withdraw the Proposed AD

    The commenter, the manufacturer, states that all affected airplanes 
have already complied with the requirements of the proposed AD. 
Therefore, the commenter requests that the FAA withdraw the proposed 
AD.
    The FAA does not agree. We acknowledge that the manufacturer has 
stated that all affected airplanes have accomplished the actions 
specified in Cessna Service Bulletin SB750-53-19, dated January 20, 
2000 (the appropriate service information specified in the final rule). 
However, we have determined that it is necessary to issue a final rule 
to prevent an inadvertent installation of a bulkhead web doubler having 
part number (P/N) 6711093-38 on any airplane. As explained in the 
preamble of the proposed AD, installation of that doubler could cause 
jamming of the roll control system (ailerons and spoilers) and result 
in reduced controllability of the airplane. Therefore, no change to the 
final rule is necessary.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that approximately 95 Cessna Model 750 airplanes 
of U.S. registry will be affected by this AD, that it will take 
approximately 8 work hours per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. The 
manufacturer has committed previously to its customers that it will 
bear the cost of replacement parts. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $45,600, or $480 
per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from 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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2001-07-04  Cessna Aircraft Company: Amendment 39-12169. Docket 
2000-NM-63-AD.

    Applicability: Model 750 airplanes, having manufacturer's serial 
numbers -0001 through -0102 inclusive, certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent jamming of the roll control system (ailerons and 
spoilers), which could result in reduced controllability of the 
airplane, accomplish the following:

Inspection and Removal

    (a) Within 200 flight hours or 180 days after the effective date 
of this AD, whichever occurs first, inspect the bulkhead web for an 
existing round bulkhead web doubler, in accordance with the 
Accomplishment Instructions of Cessna Service Bulletin SB750-53-19, 
dated January 20, 2000. If there is a round bulkhead web doubler 
having part number (P/N) 6711093-38, prior to further flight, remove 
the doubler in accordance with the service bulletin.

Installation

    (b) Within 200 flight hours or 180 days after the effective date 
of this AD, whichever occurs first, install a new right bulkhead web 
doubler having P/N 6791213-4 and a left bulkhead web doubler having 
P/N 6791213-3 and enlarge the lightening holes, in accordance with 
the Accomplishment Instructions of Cessna Service Bulletin SB750-53-
19, dated January 20, 2000.

Spares

    (c) As of the effective date of this AD, no person shall install 
a bulkhead web doubler having P/N 6711093-38, on any airplane.

Alternative Method of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Wichita Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Wichita ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.


[[Page 18523]]



Special Flight Permits

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

Incorporation by Reference

    (f) The actions shall be done in accordance with Cessna Service 
Bulletin SB750-53-19, including Supplemental Data, dated January 20, 
2000. This incorporation by reference was approved by the Director 
of the Federal Register 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 7706, Wichita, Kansas 67277. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Wichita Aircraft Certification Office, 
1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.

Effective Date

    (g) This amendment becomes effective on May 15, 2001.

    Issued in Renton, Washington, on April 2, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-8611 Filed 4-9-01; 8:45 am]
BILLING CODE 4910-13-P

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