[Federal Register Volume 60, Number 88 (Monday, May 8, 1995)]
[Rules and Regulations]
[Pages 22496-22498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-10833]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-CE-06-AD; Amendment 39-9217; AD 95-09-13]
Airworthiness Directives; Cessna Aircraft Company Models T303,
402C, 404, 414A, and 421C Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes AD 93-05-03, which currently
requires repetitively inspecting each fuel inlet float valve in
accordance with certain test procedures on Cessna Aircraft Company
(Cessna) Models T303, 402C, 404, 414A, and 421C airplanes, and
replacing any valve that does not pass this test. The manufacturer has
developed fuel inlet float valves of improved design, and the Federal
Aviation Administration (FAA) has determined that the improved valves
should be installed to reduce the number of repetitive tests currently
required by AD 93-05-03. This action requires installing these fuel
inlet float valves of improved design. The actions specified by this AD
are intended to prevent possible loss of engine power caused by failure
of a fuel inlet float valve.
DATES: Effective June 14, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 14, 1995.
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. Charles D. Riddle, Aerospace
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport
Road, Room 100, Wichita, Kansas 67209; telephone (316) 946-4144;
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 Models T303, 401C, 404, 414A, and 421C airplanes was
published in the Federal Register on September 19, 1994 (59 FR 47818).
The action proposed to require replacing the fuel inlet float valves
with parts of improved design or modifying the existing part and
periodically accomplishing functional tests to assure proper operation.
Accomplishment of the proposed actions would be in accordance with the
ACCOMPLISHMENT INSTRUCTIONS supplement to Cessna Service Bulletin (SB)
MEB93-10, dated December 3, 1993.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
Since issuance of the proposal, the manufacturer has revised Cessna
SB MEB93-10 to incorporate editorial corrections and add serial number
689 to the Cessna Model 402C airplane applicability list. Cessna has
informed the FAA that improved design fuel valves have been
incorporated on this airplane at Cessna's maintenance facilities.
After careful review of all available information, the FAA has
determined that air safety and the public interest require the adoption
of the rule as proposed except for minor editorial corrections and the
incorporation of the service bulletin revision. The FAA has determined
that the minor editorial [[Page 22497]] corrections and the
incorporation of the revised service bulletin will not add any
additional burden upon the public than was already proposed. The
addition of serial number 689 of the Cessna Model 402C airplane does
not add any additional burden upon the public because the airplane
operator already has incorporated the actions specified by this AD.
The replacement compliance time is presented in calendar time
instead of hours time-in-service (TIS). Operators in commuter service
can put up to 200 hours TIS in one calendar month while a general
aviation operator may not utilize the airplane 200 hours TIS in one
year. The calendar time compliance will allow commuter operators the
option of accomplishing the actions to coincide with regularly
scheduled maintenance.
The FAA estimates that 1,642 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 22 workhours per
airplane to accomplish the required action, and that the average labor
rate is approximately $60 an hour. Parts cost approximately $3,144 per
airplane. Based on these figures, the total cost impact of the AD on
U.S. operators is estimated to be $7,329,888. This figure is based on
the assumption that no affected airplane owner/operator has
accomplished the required valve installation.
Cessna has informed the FAA that enough improved fuel valves have
been sold to equip approximately 1,041 of the affected airplanes.
Assuming that these valves are installed on Cessna Models T303, 402C,
404, 414A, and 421C airplanes, the cost impact upon U.S. operators
would be reduced from $7,329,888 to $2,682,864.
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 93-05-03, Amendment 39-
8508 (58 FR 13406, March 11, 1993), and by adding a new airworthiness
directive to read as follows:
95-09-13 Cessna Aircraft Company: Amendment 39-9217; Docket No. 94-
CE-06-AD. Supersedes AD 93-05-03, Amendment 39-8508.
Applicability: The following model and serial number airplanes,
certificated in any category:
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Model Serial Nos.
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T303 T30300001 through T30300315.
402C 402C0001 through 402C1020, and 689.
404 404-0001 through 404-0859.
414A 414A0001 through 414A1212.
421C 421C0001 through 421C1807.
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Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To prevent possible loss of engine power caused by failure of a
fuel inlet float valve, accomplish the following:
(a) For airplanes equipped with fuel inlet float valve part
numbers (P/N) 9910242-1, 9910242-4, 9910242-5, 9910242-6, 9910242-7,
9910242-8, 9910242-205, 9910242-206, 9910242-207, and 9910242-208,
accomplish the following:
(1) Within the next 200 hours time-in-service (TIS) after the
effective date of this AD, unless already accomplished (compliance
with AD 93-05-03), perform the appropriate valve test in accordance
with paragraph 2. Functional Test Procedure or paragraph 3.
Installation Test Procedure in the Cessna MEB93-10R1 ACCOMPLISHMENT
INSTRUCTIONS supplement to Cessna Service Bulletin (SB) MEB93-10,
Revision 1, Original Issue: December 3, 1993; Revision 1: March 31,
1995. Accomplish these tests thereafter at intervals not to exceed
200 hours TIS until the fuel inlet float valves are replaced with a
P/N 9910242-11 or P/N 9910242-12 valve, and then accomplish the
appropriate valve test at intervals not to exceed 600 hours TIS.
(2) Within 12 calendar months after accumulating 1,800 hours TIS
on a fuel inlet float valve or within the next 12 calendar months
after the effective date of this AD, whichever occurs later, replace
the valve with a P/N 9910242-11 or P/N 9910242-12 fuel inlet float
valve in accordance with paragraph 4. Valve Replacement in the
Cessna MEB93-10R1 ACCOMPLISHMENT INSTRUCTIONS supplement to Cessna
Service Bulletin (SB) MEB93-10, Revision 1, Original Issue: December
3, 1993; Revision 1: March 31, 1995. Thereafter, accomplish either
the functional or installation test required by paragraph (a)(1) of
this AD at intervals not to exceed 600 hours.
Note 1: If the number of hours TIS accumulated on a fuel inlet
float valve is unknown, airplane hours TIS may be used.
(b) For airplanes equipped with fuel inlet float valve, P/N
9910242-9 or P/N 9910242-10, accomplish the following:
(1) Within the next 200 hours TIS after the effective date of
this AD, unless already accomplished (compliance with AD 93-05-03),
perform the appropriate valve test in accordance with paragraph 2.
Functional Test Procedure or paragraph 3. Installation Test
Procedure in the Cessna MEB93-10R1 ACCOMPLISHMENT INSTRUCTIONS
supplement to Cessna Service Bulletin (SB) MEB93-10, Revision 1,
Original Issue: December 3, 1993; Revision 1: March 31, 1995.
Accomplish the appropriate valve test thereafter at intervals not to
exceed 200 hours TIS until the fuel inlet float valves are modified
as specified in paragraph (b)(2) of this AD, and then accomplish the
appropriate valve test at intervals not to exceed 600 hours TIS.
(2) Within 12 calendar months after the effective date of this
AD, install the K74D retainer kit in accordance with PROCEDURE No.
P74D, which is included with the Cessna MEB93-10R1 ACCOMPLISHMENT
INSTRUCTIONS supplement to Cessna Service Bulletin (SB) MEB93-10,
Revision 1, Original Issue: December 3, 1993; Revision 1: March 31,
1995. Thereafter, accomplish the functional and installation tests
required by paragraph (b)(1) of this AD at intervals not to exceed
600 hours.
Note 2: Installation of the K74D retainer kit modifies the P/N
9910242-9 or P/N 9910242-10 fuel inlet float valves to the P/N
9910242-11 or P/N 9910242-12 configuration.
(c) For valves failing any repetitive installation or functional
test required by paragraph (a)(1), (a)(2), (b)(1), and (b)(2) of
this AD, prior to further flight, accomplish the following (unless
parts are not available and then comply with the requirements of
paragraph (d) of this AD):
(1) Replace the fuel inlet float valve with a P/N 9910242-11 or
P/N 9910242-12 valve in accordance with paragraph 4. Valve
[[Page 22498]] Replacement in the Cessna MEB93-10R1 ACCOMPLISHMENT
INSTRUCTIONS supplement to Cessna Service Bulletin (SB) MEB93-10,
Revision 1, Original Issue: December 3, 1993; Revision 1: March 31,
1995.
(2) Accomplish the installation test contained in paragraph 3.
Installation Test Procedure in the Cessna MEB93-10R1 ACCOMPLISHMENT
INSTRUCTIONS supplement to Cessna Service Bulletin (SB) MEB93-10,
Revision 1, Original Issue: December 3, 1993; Revision 1: March 31,
1995. Accomplish the appropriate valve test thereafter at intervals
not to exceed 600 hours TIS.
(d) If any fuel valve replacement is necessary and the
replacement parts are not available, accomplish the following
provided the parts have been ordered from the manufacturer and are
installed within 25 hours TIS after availability:
(1) Incorporate the following into the Limitations Section of
the Pilots Operating Handbook (POH) and FAA-approved Airplane Flight
Manual (AFM):
(i) For the Model T303 airplanes: Unusable Fuel: Indicated fuel
quantity below 36 pounds (6 gallons) in each main tank is unusable.
(ii) For the Models 402C, 404, 414A, and 421C airplanes:
Unusable Fuel: Indicated fuel quantity below 90 pounds (15 gallons)
in each main tank is unusable.
(iii) For the Model 404 airplanes: Fuel Quantity: Minimum
indicated fuel quantity for takeoff is 228 pounds (38 gallons) in
each main tank.
(iv) For the Models 402C, 414A, and 421C airplanes: Fuel
Quantity: Minimum indicated fuel quantity for takeoff is 210 pounds
(35 gallons) in each main tank.
(2) Fabricate placards, as applicable, with the following words
in letters at least 0.10-inch in height and install these placards
within the pilot's clear view on the instrument panel in close
proximity to the fuel quantity gage:
(i) For Models 402C, 404, 414A, and 421C airplanes: ``UNUSABLE
FUEL--INDICATED FUEL QUANTITY BELOW 90 POUNDS (15 GALLONS) IN EACH
MAIN TANK IS UNUSABLE''.
(ii) For Model T303 airplanes: ``UNUSABLE FUEL--INDICATED FUEL
QUANTITY BELOW 36 POUNDS (6 GALLONS) IN EACH MAIN TANK IS
UNUSABLE''.
(3) For the Model 404 airplanes, fabricate four placards with
the following in letters at least 0.10- inch in height: ``157 GAL''.
Install these placards covering the four existing ``172 GAL''
markings on the existing placard around the engine fuel selector
handles.
(4) For the Models 402C, 414A, and 421C airplanes, fabricate
four placards with the following in letters at least 0.10-inch in
height: ``88 GAL''. Install these placards covering the four
existing ``103 GAL'' markings on the existing placard around the
engine fuel selector handles.
(5) For the Model T303 airplanes, fabricate the following
placards in letters at least 0.10-inch in height:
(i) ``423 LBS'' (2 placards). Install these placards covering
the two existing ``459 LBS'' markings on the existing placard around
the engine fuel selector handles.
(ii) ``363 LBS'' (1 placard). Install this placard covering the
existing ``399 LBS'' marking on the existing placard around the
engine fuel selector handles.
(6) For all affected Model airplanes, fabricate a placard with
the following words in letters at least 0.10-inch in height and
install this placard within the pilot's clear view on the instrument
panel: ``ROLLING, TURNING TAKEOFFS ARE PROHIBITED.''
Note 3: The placard requirements may already be accomplished in
accordance with either superseded AD 92-27-20 or AD 93-05-03
(superseded by this action). These placard requirements are
eliminated upon installation of the improved fuel valves as required
by this AD.
Note 4: The repetitive functional or installation test is not
required if parts are not available and the requirements of
paragraph (d) of this AD (including all subparagraphs) are complied
with.
(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
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Manager, Wichita
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 5: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(g) The installation, replacement, and tests required by this AD
shall be done in accordance with the Cessna MEB93-10R1
ACCOMPLISHMENT INSTRUCTIONS supplement to Cessna Service Bulletin
(SB) MEB93-10, Revision 1, Original Issue: December 3, 1993;
Revision 1: March 31, 1995. 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 the
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 (39-9217) supersedes AD 93-05-03, Amendment
39-8508.
(i) This amendment (39-9217) becomes effective on June 14, 1995.
Issued in Kansas City, Missouri, on April 26, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-10833 Filed 5-5-95; 8:45 am]
BILLING CODE 4910-13-U
