[Federal Register Volume 76, Number 64 (Monday, April 4, 2011)]
[Rules and Regulations]
[Pages 18376-18378]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-7729]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0302; Directorate Identifier 2011-CE-008-AD;
Amendment 39-16650; AD 2011-07-13]
RIN 2120-AA64
Airworthiness Directives; CPAC, Inc. (Type Certificate Formerly
Held by Commander Aircraft Corporation, Gulfstream Aerospace
Corporation, and Rockwell International) Models 112, 112B, 112TC,
112TCA, 114, 114A, 114B, and 114TC Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD requires an inspection of the elevator
spar for cracks and, if any crack is found, either replacement with a
serviceable elevator spar that is found free of cracks or repair/
modification with an FAA-approved method. This AD also requires
reporting to the FAA the results of the inspection. This AD was
prompted by reports of a total of nine elevator spar cracks across
seven of the affected airplanes, including a crack of 2.35 inches just
below the outboard hinge of the right-hand elevator. We are issuing
this AD to prevent structural failure of the elevator spar due to such
cracking, which could result in separation of the elevator from the
airplane with consequent loss of control.
DATES: This AD is effective April 4, 2011.
We must receive comments on this AD by May 19, 2011.
ADDRESSES: You may send comments by any of the following methods:
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.
Examining the AD Docket
You may examine the AD docket 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 AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone: 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, Senior Aerospace
Engineer, Wichita Aircraft Certification Office (ACO), FAA, 1801
Airport Road, Room 100; phone: (316) 946-4155; fax: (316) 946-4107; e-
mail: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA has received a report from CPAC, Inc. describing a crack of
2.35 inches just below the outboard hinge of the right-hand elevator on
a CPAC, Inc. Model 114 airplane. The Models 112, 112B, 112TC, 112TCA,
114, 114A, 114B, and 114TC have the same design of the elevator spar
and are all part of Type Certificate A12SO. There have been a total of
nine elevator spar cracks across seven of these airplanes.
Type Certificate A12SO does not include Models 112A and 115. The
Model 112A is a Rockwell ``marketing name'' for the Model 112. The
Model 115 is a Rockwell ``marketing name'' for the Model 114.
If not corrected, structural failure of the elevator spar could
result in separation of the elevator from the airplane with consequent
loss of control.
Relevant Service Information
We have included in this AD procedures for removing the elevator
and inspecting the forward and aft sides of the right-hand and left-
hand elevator forward spar web near and around the outboard hinge area.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires an inspection of the elevator spar for cracks and,
if any crack is found, replacement of the elevator spar with a
serviceable spar that is found free of cracks or repair/modification
with an FAA-approved method. This AD also requires reporting to the FAA
of the results of the inspection.
Interim Action
We consider this AD interim action. We are requiring a one-time
inspection of the elevator spar with a report to the FAA of the
results. We will work with the type certificate holder to evaluate that
information to determine repetitive inspection intervals and subsequent
terminating action. Based on this evaluation, we may initiate further
rulemaking action to address the unsafe condition identified in this
AD.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
structural failure of the elevator spar would result in potential
separation of the elevator with consequent loss of control.
Therefore, we find that notice and opportunity for prior public
comment are impracticable and that good cause exists for making this
amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2011-0302 and
Directorate Identifier 2011-CE-008-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will
consider all comments received by the closing date and may amend this
AD because 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 about this AD.
[[Page 18377]]
Costs of Compliance
We estimate that this AD affects 773 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspection of the elevator spar..... 8 work-hours x $85 per N/A $680 $525,640
hour = $680.
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Currently, there is no FAA-approved repair/modification for a
cracked elevator spar. Further flight is prohibited until an FAA-
approved repair/modification is submitted to the FAA and FAA-approved.
A cracked elevator spar could be replaced with a serviceable one if one
is available. The FAA does not have availability and cost information
on serviceable elevator spars. Therefore, at this time, the FAA has no
way of determining any on-condition costs associated with cracks found
in the elevator spar.
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
This AD will not have federalism implications under Executive Order
13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2011-07-13 CPAC, Inc. (Type Certificate Formerly Held by Commander
Aircraft Corporation, Gulfstream Aerospace Corporation, and Rockwell
International): Amendment 39-16650; Docket No. FAA-2011-0302;
Directorate Identifier 2011-CE-008-AD.
Effective Date
(a) This AD is effective April 4, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to CPAC, Inc. (type certificate formerly
held by Commander Aircraft Corporation, Gulfstream Aerospace
Corporation, and Rockwell International) Models 112, 112B, 112TC,
112TCA, 114, 114A, 114B, and 114TC airplanes, all serial numbers,
certificated in any category. Type Certificate No. A12SO does not
include Models 112A and 115. The Model 112A is a Rockwell
``marketing name'' for the Model 112. The Model 115 is a Rockwell
``marketing name'' for the Model 114. Since they are type-
certificated as Model 112 and Model 114, this AD is applicable to
the Models 112A and 115.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 55, Stabilizers.
Unsafe Condition
(e) This AD was prompted by reports of a total of nine elevator
spar cracks across seven of the affected airplanes, including a
crack of 2.35 inches just below the outboard hinge of the right-hand
elevator. We are issuing this AD to prevent structural failure of
the elevator spar due to such cracking, which could result in
separation of the elevator from the airplane with consequent loss of
control.
Compliance
(f) Comply with this AD within the compliance times specified.
Inspection/Repair
(g) Within the next 5 hours time-in-service after the effective
date of this AD, do the following for the left-hand and right-hand
elevators:
(1) Disconnect the elevator trim pushrod at the trim tab.
(2) Remove the hinge bolts at the horizontal stabilizer points.
(3) Remove six screws and two bolts at the inboard end of the
elevator and remove the elevator.
(4) Remove all fasteners common to the elevator outboard aft end
rib, part number (P/N) 44330, and elevator skin, P/N 44323.
(5) Remove the remaining two fasteners common to the elevator
outboard aft End rib (P/N 44330) and the elevator spar, P/N 44211.
(6) Remove the elevator aft end rib, P/N 44330, to gain access
to the aft side of the elevator spar.
(7) Remove the four bolts, washers, and nuts that secure the
outboard elevator hinge, P/N 44285.
(8) Remove elevator hinge, P/N 44285, from the elevator spar.
(9) Clean in and around the location of the outboard bracket on
the elevator spar and visually inspect for cracks. Use a 10X
magnifier to facilitate the detection of any crack.
(10) If cracks are found, before further flight, do the
following:
(i) Either replace the elevator spar with a serviceable spar
that is found free of cracks or repair/modify the elevator spar
following a procedure approved for this AD by the FAA, Wichita
Aircraft Certification Office (ACO); and
(ii) Reassemble the elevator assembly, rebalance the elevator,
and reinstall on the
[[Page 18378]]
airplane following standard repair practices. Ensure elevator
rigging is within tolerance, and that the system operates with ease,
smoothness, and positiveness appropriate to its function.
Note: Elevator rigging and rebalancing, torque values, and other
general maintenance information can be found in the maintenance
manual.
Reporting Requirement
(h) Report the results of the inspection to the FAA, Wichita
ACO, FAA, Attn: T.N. Baktha, Senior Aerospace Engineer, 1801 Airport
Road, Room 100; phone: (316) 946-4155; fax: (316) 946-4107; e-mail:
[email protected]. Include the following information:
(1) Airplane model and serial number.
(2) Hours time-in-service at time of inspection.
(3) Annotate any cracking found, including the exact location
and length of any cracks.
(4) Any installations, repairs, modifications, etc. that have
been done on your airplane in the elevator spar area or that could
have affected the elevator spar.
(5) Type of operation primarily flown in.
Paperwork Reduction Act Burden Statement
(i) A federal agency may not conduct or sponsor, and a person is
not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Wichita ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the ACO, send it to the attention of the person
identified in the Related Information section of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
Related Information
(k) For more information about this AD, contact T.N. Baktha,
Senior Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room
100; phone: (316) 946-4186; fax: (316) 946-4107; e-mail:
[email protected].
Issued in Kansas City, Missouri, on March 28, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011-7729 Filed 4-1-11; 8:45 am]
BILLING CODE 4910-13-P