Airworthiness Directives; The Cessna Aircraft Company Model 750 Airplanes, 17879-17882 [2010-7943]
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17879
Proposed Rules
Federal Register
Vol. 75, No. 67
Thursday, April 8, 2010
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0380; Directorate
Identifier 2009–NM–009–AD]
RIN 2120–AA64
Airworthiness Directives; The Cessna
Aircraft Company Model 750 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Model
750 airplanes. The existing AD currently
requires inspecting the inboard-hinge
brackets of the left and right elevators
for cracking and doing related
investigative and corrective actions if
necessary. For certain airplanes, this
proposed AD would require inspecting
for cracks and corrosion of the bracket
of the inboard horizontal stabilizer and
measuring the lug thickness of the
horizontal stabilizer hinges; doing
corrective actions if necessary;
modifying the left and right elevators
and left and right horizontal stabilizer.
For all airplanes, this proposed AD
would require replacing the existing
elevator assemblies with new elevator
assemblies, which would terminate the
requirements of the existing AD. This
proposed AD would also revise the
applicability to remove certain
airplanes. This proposed AD results
from a report of cracking and corrosion
found on the elevator inboard-hinge
brackets and the horizontal stabilizer
hinges. We are issuing this AD to
prevent such cracking and corrosion of
the elevator inboard-hinge brackets and
the horizontal stabilizer hinges, which
could result in structural failure of the
elevators and consequent loss of control
of the airplane.
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SUMMARY:
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DATES: We must receive comments on
this proposed AD by May 24, 2010.
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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 service information identified in
this proposed AD, contact Cessna
Aircraft Co., P.O. Box 7706, Wichita,
Kansas 67277; telephone 316–517–6215;
fax 316–517–5802; e-mail
citationpubs@cessna.textron.com;
Internet https://
www.cessnasupport.com/newlogin.html.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA,
call 425–227–1221.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: T.N.
Baktha, Aerospace Engineer, Airframe
Branch, ACE–118W, FAA, Wichita
Aircraft Certification Office, 1801
Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas 67209;
telephone (316) 946–4155; fax (316)
946–4107.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2010–0380; Directorate Identifier
2009–NM–009–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On October 26, 2006, we issued AD
2006–23–05, Amendment 39–14817 (71
FR 65047, November 7, 2006), for all
The Cessna Aircraft Company Model
750 airplanes. That AD requires
inspecting the inboard-hinge brackets of
the left and right elevators for cracking,
and doing related investigative and
corrective actions if necessary. That AD
resulted from a report of cracking found
on the elevator inboard-hinge brackets.
We issued that AD to detect and correct
cracking of the elevator inboard-hinge
brackets, which could result in
structural failure of the elevators and
consequent loss of control of the
airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2006–23–05
explains that we considered the
requirements ‘‘interim action’’ and were
considering further rulemaking if a final
action is identified. We now have
determined that further rulemaking is
indeed necessary, and this proposed AD
follows from that determination.
Relevant Service Information
We have reviewed Cessna Service
Bulletin SB750–27–62, Revision 3,
dated August 21, 2009, including
Service Bulletin Supplemental Data,
Revision D, dated September 18, 2009.
That service bulletin describes
procedures for the following:
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Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules
• For certain airplanes, doing an eddy
current inspection for cracks of the
bracket of the inboard horizontal
stabilizer; and corrective action, if
necessary, which is replacing any
cracked bracket of the inboard
horizontal stabilizer with a serviceable
bracket.
• For certain airplanes, measuring the
lug thickness of the horizontal stabilizer
hinges; and corrective action, if
necessary, which is replacing the
bearing plate with a serviceable bearing
plate if the lug thickness is not within
the acceptable tolerance range.
• For certain airplanes, modifying the
left and right horizontal stabilizer, and
adding the modification part number of
the horizontal stabilizer to the
modification section of the MS27253–1
identification plate.
• For all airplanes, replacing the left
and right elevator assemblies with new
elevator assemblies.
Accomplishment of the applicable
actions specified in Cessna Service
Bulletin SB750–27–62, Revision 3,
dated August 21, 2009, eliminates the
need for the actions required by AD
2006–23–05.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to develop on
other airplanes of the same type design.
For this reason, we are proposing this
AD, which would supersede AD 2006–
23–05 and would retain the
requirements of the existing AD. This
proposed AD removes certain airplanes
from the applicability of the existing
AD. Cessna Model 750 airplanes with
serial number 750–306 and subsequent
are no longer subject to the
requirements of this AD as Cessna has
incorporated the applicable
requirements in production. This
proposed AD would also require
accomplishing the actions specified in
the ‘‘Relevant Service Information’’
described previously, except as
discussed under ‘‘Differences Between
the Proposed AD and Service Bulletin.’’
cracked brackets. This proposed AD
would also require an inspection for
corrosion and replacement of any
corroded brackets.
Change to Existing AD
This proposed AD would retain the
requirements of AD 2006–23–05. Since
AD 2006–23–05 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2006–23–05
Corresponding
requirement in this
proposed AD
paragraph (d)
paragraph (e)
paragraph (f)
paragraph (g)
paragraph (h)
paragraph (i)
paragraph (e)
paragraph (f)
paragraph (g)
paragraph (h)
paragraph (i)
paragraph (j)
Differences Between the Proposed AD
and Service Bulletin
Cessna Service Bulletin SB750–27–62,
Revision 3, dated August 21, 2009,
specifies to do eddy current inspection
for cracks of the bracket of the inboard
horizontal stabilizer and replace any
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Inspection (required by AD
2006–23–05).
Modification and Replacement (new proposed actions).
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Work hours
2 ..................
$85
Up to 200 ....
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
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Parts
Cost per airplane
Number of
U.S.-registered
airplanes
$0 ......................................
$170 ............
253
$43,010.
The manufacturer states
that it will supply parts
to the operators at no
cost.
Up to
$17,000.
253
Up to 4,301,000.
Average labor
rate per hour
Action
products identified in this rulemaking
action.
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
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Fleet cost
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. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
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:
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Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14817 (71 FR
65047, November 7, 2006) and adding
the following new AD:
The Cessna Aircraft Company: Docket No.
FAA–2010–0380; Directorate Identifier
2009–NM–009–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by May 24, 2010.
Affected ADs
(b) This AD supersedes AD 2006–23–05,
Amendment 39–14817.
Applicability
(c) This AD applies to The Cessna Aircraft
Company Model 750 airplanes, certificated in
any category, as identified in Cessna Service
Bulletin SB750–27–62, Revision 3, dated
August 21, 2009.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight Controls.
Unsafe Condition
(e) This AD results from a report of
cracking and corrosion found on the elevator
inboard-hinge brackets and the horizontal
stabilizer hinges. The Federal Aviation
Administration is issuing this AD to prevent
cracking and corrosion of the elevator
inboard-hinge brackets and the horizontal
stabilizer hinges, which could result in
structural failure of the elevators and
consequent loss of control of the airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
RESTATEMENT OF REQUIREMENTS OF
AD 2006–23–05, WITH NO CHANGES:
Inspection
(g) After the airplane accumulates 2,500
total flight hours: Perform a general visual
inspection for cracking of the inboard-hinge
brackets of the left and right elevators in
accordance with the Accomplishment
Instructions of Cessna Alert Service Letter
ASL750–27–21, dated October 13, 2006. Do
the inspection before the airplane
accumulates 3,000 total flight hours, or
within 10 flight hours after November 22,
2006 (the effective date of AD 2006–23–05),
whichever is later.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to enhance visual access to
all exposed surfaces in the inspection area.
This level of inspection is made under
normally available lighting conditions such
as daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Related Investigative and Corrective Actions
(h) If any crack is found during the
inspection required by paragraph (g) of this
AD: Before further flight, perform an eddy
current inspection of the inboard-hinge
brackets to determine the crack length, in
accordance with the Accomplishment
Instructions of Cessna Alert Service Letter
ASL750–27–21, dated October 13, 2006; and
do the actions specified in paragraph (h)(1)
or (h)(2) of this AD, as applicable, at the time
specified. All corrective actions must be done
using a method approved by the Manager,
Wichita Aircraft Certification Office (ACO),
FAA. For a replacement method to be
approved by the Manager, Wichita ACO, as
required by this paragraph, the Manager’s
approval letter must specifically refer to this
AD.
(1) If the crack is 0.30 inch or more:
Replace the bracket before further flight.
(2) If the crack is less than 0.30 inch:
Continued flight for a maximum of 10 flight
hours for repositioning of the airplane and
replacement of the bracket is allowed, within
the restricted flight envelope included in the
attachment to Cessna Alert Service Letter
ASL750–27–21, dated October 13, 2006,
titled ‘‘Flight Restrictions.’’
Special Flight Permits
(i) Special flight permits, as described in
Section 39.23 of the Federal Aviation
Regulations (14 CFR 39.23), are allowed with
the limitations required by paragraph (h)(2)
of this AD.
No Reporting or Return of Parts to
Manufacturer
(j) Cessna Alert Service Letter ASL750–27–
21, dated October 13, 2006, specifies
submitting a sheet related to inspection
results to the manufacturer; this AD does not
include that requirement. The service letter
also specifies sending the elevator assembly
to the manufacturer for replacement of the
inboard-hinge bracket if a crack is found that
is 0.30 inch or more; however, this AD
requires corrective actions be done using a
method approved by us.
NEW REQUIREMENTS OF THIS AD:
(k) Within 60 months after the effective
date of this AD, do the applicable actions
required by paragraphs (k)(1), (k)(2), (k)(3),
and (k)(4) of this AD, in accordance with the
Accomplishment Instructions of Cessna
Service Bulletin SB750–27–62, Revision 3,
dated August 21, 2009. Accomplishing the
actions required by paragraph (k) of this AD
terminates the requirements of paragraphs (g)
through (j) of this AD.
(1) For all airplanes except those having
S/Ns 288 through 305 inclusive: Do an eddy
current inspection for cracks and corrosion of
the bracket of the inboard horizontal
stabilizer. Before further flight, replace any
cracked or corroded bracket of the inboard
horizontal stabilizer with a serviceable
bracket.
(2) For all airplanes except those having
S/Ns 288 through 305 inclusive: Measure the
lug thickness of the horizontal stabilizer
hinges. If the lug thickness is not within the
acceptable tolerance range, as identified in
Cessna Service Bulletin SB750–27–62,
Revision 3, dated August 21, 2009, before
further flight, replace the bearing plate with
a serviceable bearing plate.
(3) For all airplanes except those having
S/Ns 288 through 305 inclusive: Modify the
left and right horizontal stabilizer; and add
the modification part number of the
horizontal stabilizer to the modification
section of the MS27253–1 identification
plate.
(4) For all airplanes: Replace the existing
elevator assemblies with new elevator
assemblies having part numbers 6734000–17
(for the left side) and 6734000–18 (for the
right side).
Credit for Actions Done Using the Previous
Service Information
(l) Actions accomplished before the
effective date of this AD in accordance with
the service bulletins identified in Table 1 of
this AD are considered acceptable for
compliance with the corresponding
requirements of paragraph (k) of this AD.
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TABLE 1—CREDIT FOR PREVIOUS SERVICE BULLETINS
Service Bulletin
Revision level
Cessna Service Bulletin SB750–27–62 .........................................................................................
Cessna Service Bulletin SB750–27–62 .........................................................................................
Cessna Service Bulletin SB750–27–62 .........................................................................................
Original ........................
1 ..................................
2 ..................................
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08APP1
Date
October 13, 2008.
October 22, 2008.
December 17, 2008.
17882
Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(m)(1) 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: T.N.
Baktha, Aerospace Engineer, Airframe
Branch, ACE–118W, FAA, Wichita ACO,
1801 Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas 67209; telephone
(316) 946–4155; fax (316) 946–4107.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
Issued in Renton, Washington, on April 1,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–7943 Filed 4–7–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0379; Directorate
Identifier 2009–NM–210–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–300, –400, and
–500 Series Airplanes
sroberts on DSKD5P82C1PROD with PROPOSALS
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Model
737–300, –400, and –500 series
airplanes. The existing AD currently
requires inspecting to determine if
certain carriage spindles are installed,
repetitive inspections for corrosion and
indications of corrosion on affected
carriage spindles, and if necessary,
related investigative and corrective
actions. The existing AD also provides
an optional terminating action. This
proposed AD would mandate the
optional terminating action, which
would eliminate the need for the
repetitive inspections. The proposed AD
results from reports of corrosion found
on carriage spindles that are located on
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the outboard trailing edge flaps. We are
proposing this AD to detect and correct
corrosion of the carriage spindle, which
could result in fracture. Fracture of both
the inboard and outboard carriage
spindles, in the forward ends through
the large diameters, on a flap, could
adversely affect the airplane’s continued
safe flight and landing.
DATES: We must receive comments on
this proposed AD by May 24, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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 service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590.
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SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2010–0379; Directorate Identifier
2009–NM–210–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On October 26, 2009, we issued AD
2009–23–10, Amendment 39–16084 (74
FR 57564, November 9, 2009), for all
Model 737–300, –400, and –500 series
airplanes. That AD requires inspecting
to determine if certain carriage spindles
are installed, repetitive inspections for
corrosion and indications of corrosion
on affected carriage spindles, and if
necessary, related investigative and
corrective actions. That AD also
provides an optional terminating action.
That AD resulted from reports of
corrosion found on carriage spindles
that are located on the outboard trailing
edge flaps. We issued that AD to detect
and correct corrosion of the carriage
spindle, which could result in fracture.
Fracture of both the inboard and
outboard carriage spindles, in the
forward ends through the large
diameters, on a flap, could adversely
affect the airplane’s continued safe
flight and landing.
Actions Since Existing AD Was Issued
The preamble to AD 2009–23–10
explains that we consider the
requirements ‘‘interim action’’ and were
considering further rulemaking. We now
have determined that further
rulemaking is indeed necessary, and
this proposed AD follows from that
determination.
Boeing Commercial Airplanes has
received an Organization Designation
Authorization (ODA), which replaces
their previous designation as a
Delegation Option Authorization (DOA)
holder. We have revised paragraph (l)(3)
of this AD to delegate the authority to
approve an alternative method of
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]]>Agencies
[Federal Register Volume 75, Number 67 (Thursday, April 8, 2010)]
[Proposed Rules]
[Pages 17879-17882]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-7943]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 75, No. 67 / Thursday, April 8, 2010 /
Proposed Rules
[[Page 17879]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0380; Directorate Identifier 2009-NM-009-AD]
RIN 2120-AA64
Airworthiness Directives; The Cessna Aircraft Company Model 750
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Model 750 airplanes. The existing AD
currently requires inspecting the inboard-hinge brackets of the left
and right elevators for cracking and doing related investigative and
corrective actions if necessary. For certain airplanes, this proposed
AD would require inspecting for cracks and corrosion of the bracket of
the inboard horizontal stabilizer and measuring the lug thickness of
the horizontal stabilizer hinges; doing corrective actions if
necessary; modifying the left and right elevators and left and right
horizontal stabilizer. For all airplanes, this proposed AD would
require replacing the existing elevator assemblies with new elevator
assemblies, which would terminate the requirements of the existing AD.
This proposed AD would also revise the applicability to remove certain
airplanes. This proposed AD results from a report of cracking and
corrosion found on the elevator inboard-hinge brackets and the
horizontal stabilizer hinges. We are issuing this AD to prevent such
cracking and corrosion of the elevator inboard-hinge brackets and the
horizontal stabilizer hinges, which could result in structural failure
of the elevators and consequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by May 24, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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 service information identified in this proposed AD, contact
Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277; telephone
316-517-6215; fax 316-517-5802; e-mail citationpubs@cessna.textron.com;
Internet https://www.cessnasupport.com/newlogin.html. You may review
copies of the referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For
information on the availability of this material at the FAA, call 425-
227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://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 AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer,
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office,
1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas
67209; telephone (316) 946-4155; fax (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0380;
Directorate Identifier 2009-NM-009-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On October 26, 2006, we issued AD 2006-23-05, Amendment 39-14817
(71 FR 65047, November 7, 2006), for all The Cessna Aircraft Company
Model 750 airplanes. That AD requires inspecting the inboard-hinge
brackets of the left and right elevators for cracking, and doing
related investigative and corrective actions if necessary. That AD
resulted from a report of cracking found on the elevator inboard-hinge
brackets. We issued that AD to detect and correct cracking of the
elevator inboard-hinge brackets, which could result in structural
failure of the elevators and consequent loss of control of the
airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2006-23-05 explains that we considered the
requirements ``interim action'' and were considering further rulemaking
if a final action is identified. We now have determined that further
rulemaking is indeed necessary, and this proposed AD follows from that
determination.
Relevant Service Information
We have reviewed Cessna Service Bulletin SB750-27-62, Revision 3,
dated August 21, 2009, including Service Bulletin Supplemental Data,
Revision D, dated September 18, 2009. That service bulletin describes
procedures for the following:
[[Page 17880]]
For certain airplanes, doing an eddy current inspection
for cracks of the bracket of the inboard horizontal stabilizer; and
corrective action, if necessary, which is replacing any cracked bracket
of the inboard horizontal stabilizer with a serviceable bracket.
For certain airplanes, measuring the lug thickness of the
horizontal stabilizer hinges; and corrective action, if necessary,
which is replacing the bearing plate with a serviceable bearing plate
if the lug thickness is not within the acceptable tolerance range.
For certain airplanes, modifying the left and right
horizontal stabilizer, and adding the modification part number of the
horizontal stabilizer to the modification section of the MS27253-1
identification plate.
For all airplanes, replacing the left and right elevator
assemblies with new elevator assemblies.
Accomplishment of the applicable actions specified in Cessna
Service Bulletin SB750-27-62, Revision 3, dated August 21, 2009,
eliminates the need for the actions required by AD 2006-23-05.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2006-23-05 and would retain the requirements of the
existing AD. This proposed AD removes certain airplanes from the
applicability of the existing AD. Cessna Model 750 airplanes with
serial number 750-306 and subsequent are no longer subject to the
requirements of this AD as Cessna has incorporated the applicable
requirements in production. This proposed AD would also require
accomplishing the actions specified in the ``Relevant Service
Information'' described previously, except as discussed under
``Differences Between the Proposed AD and Service Bulletin.''
Differences Between the Proposed AD and Service Bulletin
Cessna Service Bulletin SB750-27-62, Revision 3, dated August 21,
2009, specifies to do eddy current inspection for cracks of the bracket
of the inboard horizontal stabilizer and replace any cracked brackets.
This proposed AD would also require an inspection for corrosion and
replacement of any corroded brackets.
Change to Existing AD
This proposed AD would retain the requirements of AD 2006-23-05.
Since AD 2006-23-05 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 2006-23-05 proposed AD
------------------------------------------------------------------------
paragraph (d) paragraph (e)
paragraph (e) paragraph (f)
paragraph (f) paragraph (g)
paragraph (g) paragraph (h)
paragraph (h) paragraph (i)
paragraph (i) paragraph (j)
------------------------------------------------------------------------
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per airplane registered Fleet cost
rate per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2006- 2................. $85 $0................ $170.............. 253 $43,010.
23-05).
Modification and Replacement Up to 200......... 85 The manufacturer Up to $17,000..... 253 Up to 4,301,000.
(new proposed actions). states that it
will supply parts
to the operators
at no cost.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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.
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. See the
ADDRESSES section for a location to examine the regulatory evaluation.
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:
[[Page 17881]]
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 Amendment 39-14817 (71 FR
65047, November 7, 2006) and adding the following new AD:
The Cessna Aircraft Company: Docket No. FAA-2010-0380; Directorate
Identifier 2009-NM-009-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by May 24,
2010.
Affected ADs
(b) This AD supersedes AD 2006-23-05, Amendment 39-14817.
Applicability
(c) This AD applies to The Cessna Aircraft Company Model 750
airplanes, certificated in any category, as identified in Cessna
Service Bulletin SB750-27-62, Revision 3, dated August 21, 2009.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
Controls.
Unsafe Condition
(e) This AD results from a report of cracking and corrosion
found on the elevator inboard-hinge brackets and the horizontal
stabilizer hinges. The Federal Aviation Administration is issuing
this AD to prevent cracking and corrosion of the elevator inboard-
hinge brackets and the horizontal stabilizer hinges, which could
result in structural failure of the elevators and consequent loss of
control of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
RESTATEMENT OF REQUIREMENTS OF AD 2006-23-05, WITH NO CHANGES:
Inspection
(g) After the airplane accumulates 2,500 total flight hours:
Perform a general visual inspection for cracking of the inboard-
hinge brackets of the left and right elevators in accordance with
the Accomplishment Instructions of Cessna Alert Service Letter
ASL750-27-21, dated October 13, 2006. Do the inspection before the
airplane accumulates 3,000 total flight hours, or within 10 flight
hours after November 22, 2006 (the effective date of AD 2006-23-05),
whichever is later.
Note 1: For the purposes of this AD, a general visual
inspection is: ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made from within
touching distance unless otherwise specified. A mirror may be
necessary to enhance visual access to all exposed surfaces in the
inspection area. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or droplight and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''
Related Investigative and Corrective Actions
(h) If any crack is found during the inspection required by
paragraph (g) of this AD: Before further flight, perform an eddy
current inspection of the inboard-hinge brackets to determine the
crack length, in accordance with the Accomplishment Instructions of
Cessna Alert Service Letter ASL750-27-21, dated October 13, 2006;
and do the actions specified in paragraph (h)(1) or (h)(2) of this
AD, as applicable, at the time specified. All corrective actions
must be done using a method approved by the Manager, Wichita
Aircraft Certification Office (ACO), FAA. For a replacement method
to be approved by the Manager, Wichita ACO, as required by this
paragraph, the Manager's approval letter must specifically refer to
this AD.
(1) If the crack is 0.30 inch or more: Replace the bracket
before further flight.
(2) If the crack is less than 0.30 inch: Continued flight for a
maximum of 10 flight hours for repositioning of the airplane and
replacement of the bracket is allowed, within the restricted flight
envelope included in the attachment to Cessna Alert Service Letter
ASL750-27-21, dated October 13, 2006, titled ``Flight
Restrictions.''
Special Flight Permits
(i) Special flight permits, as described in Section 39.23 of the
Federal Aviation Regulations (14 CFR 39.23), are allowed with the
limitations required by paragraph (h)(2) of this AD.
No Reporting or Return of Parts to Manufacturer
(j) Cessna Alert Service Letter ASL750-27-21, dated October 13,
2006, specifies submitting a sheet related to inspection results to
the manufacturer; this AD does not include that requirement. The
service letter also specifies sending the elevator assembly to the
manufacturer for replacement of the inboard-hinge bracket if a crack
is found that is 0.30 inch or more; however, this AD requires
corrective actions be done using a method approved by us.
NEW REQUIREMENTS OF THIS AD:
(k) Within 60 months after the effective date of this AD, do the
applicable actions required by paragraphs (k)(1), (k)(2), (k)(3),
and (k)(4) of this AD, in accordance with the Accomplishment
Instructions of Cessna Service Bulletin SB750-27-62, Revision 3,
dated August 21, 2009. Accomplishing the actions required by
paragraph (k) of this AD terminates the requirements of paragraphs
(g) through (j) of this AD.
(1) For all airplanes except those having S/Ns 288 through 305
inclusive: Do an eddy current inspection for cracks and corrosion of
the bracket of the inboard horizontal stabilizer. Before further
flight, replace any cracked or corroded bracket of the inboard
horizontal stabilizer with a serviceable bracket.
(2) For all airplanes except those having S/Ns 288 through 305
inclusive: Measure the lug thickness of the horizontal stabilizer
hinges. If the lug thickness is not within the acceptable tolerance
range, as identified in Cessna Service Bulletin SB750-27-62,
Revision 3, dated August 21, 2009, before further flight, replace
the bearing plate with a serviceable bearing plate.
(3) For all airplanes except those having S/Ns 288 through 305
inclusive: Modify the left and right horizontal stabilizer; and add
the modification part number of the horizontal stabilizer to the
modification section of the MS27253-1 identification plate.
(4) For all airplanes: Replace the existing elevator assemblies
with new elevator assemblies having part numbers 6734000-17 (for the
left side) and 6734000-18 (for the right side).
Credit for Actions Done Using the Previous Service Information
(l) Actions accomplished before the effective date of this AD in
accordance with the service bulletins identified in Table 1 of this
AD are considered acceptable for compliance with the corresponding
requirements of paragraph (k) of this AD.
Table 1--Credit for Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Cessna Service Bulletin SB750-27-62.............. Original................ October 13, 2008.
Cessna Service Bulletin SB750-27-62.............. 1....................... October 22, 2008.
Cessna Service Bulletin SB750-27-62.............. 2....................... December 17, 2008.
----------------------------------------------------------------------------------------------------------------
[[Page 17882]]
Alternative Methods of Compliance (AMOCs)
(m)(1) 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: T.N. Baktha, Aerospace Engineer, Airframe Branch, ACE-118W,
FAA, Wichita ACO, 1801 Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas 67209; telephone (316) 946-4155; fax (316)
946-4107.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
Issued in Renton, Washington, on April 1, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-7943 Filed 4-7-10; 8:45 am]
BILLING CODE 4910-13-P
