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, 18376-18378 [2011-7729]

Download as PDF 18376 Federal Register / Vol. 76, No. 64 / Monday, April 4, 2011 / Rules and Regulations Authority: 13 CFR part 120. 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. Grady B. Hedgespeth, Director, Office of Financial Assistance. [FR Doc. 2011–7862 Filed 4–1–11; 8:45 am] BILLING CODE 8025–01–P Examining the AD Docket 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: sroberts on DSK69SOYB1PROD with RULES VerDate Mar<15>2010 18:24 Apr 01, 2011 Jkt 223001 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: t.n.baktha@faa.gov. SUPPLEMENTARY INFORMATION: Discussion 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 FAAapproved 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 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, SUMMARY: 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 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. 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. PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 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 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 AD. E:\FR\FM\04APR1.SGM 04APR1 18377 Federal Register / Vol. 76, No. 64 / Monday, April 4, 2011 / Rules and Regulations 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 Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection of the elevator spar ....................... 8 work-hours × $85 per hour = $680 ............. N/A $680 $525,640 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 oncondition costs associated with cracks found in the elevator spar. sroberts on DSK69SOYB1PROD with RULES 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), VerDate Mar<15>2010 18:24 Apr 01, 2011 Jkt 223001 (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 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 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 typecertificated as Model 112 and Model 114, this AD is applicable to the Models 112A and 115. PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 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 E:\FR\FM\04APR1.SGM 04APR1 18378 Federal Register / Vol. 76, No. 64 / Monday, April 4, 2011 / Rules and Regulations 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. Issued in Kansas City, Missouri, on March 28, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. 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: t.n.baktha@faa.gov. 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. DEPARTMENT OF TRANSPORTATION sroberts on DSK69SOYB1PROD with RULES 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: t.n.baktha@faa.gov. VerDate Mar<15>2010 18:24 Apr 01, 2011 Jkt 223001 [FR Doc. 2011–7729 Filed 4–1–11; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2010–1189; Airspace Docket No. 10–AWP–19] Amendment of Class E Airspace; Taylor, AZ Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action will amend Class E airspace at Taylor Airport, Taylor, AZ, to accommodate aircraft using the CAMBO One Departure, and the Area Navigation (RNAV) standard instrument approach procedures at Taylor Airport. This will improve the safety and management of Instrument Flight Rules (IFR) operations at the airport. This action also corrects the airport names to Taylor Airport, and Show Low Regional Airport, respectively. Additionally, the geographic coordinates for Taylor Airport will be adjusted. DATES: Effective date, 0901 UTC, June 30, 2011. The Director of the Federal Register approves this incorporation by reference action under 1 CFR part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. FOR FURTHER INFORMATION CONTACT: Eldon Taylor, Federal Aviation Administration, Operations Support Group, Western Service Center, 1601 Lind Avenue, SW., Renton, WA 98057; telephone (425) 203–4537. SUPPLEMENTARY INFORMATION: SUMMARY: History On January 20, 2011, the FAA published in the Federal Register a notice of proposed rulemaking to amend controlled airspace at Taylor, AZ (76 FR 3570). Interested parties were invited to participate in this rulemaking effort by submitting written comments on the proposal to the FAA. No comments were received. Subsequent to publication, the FAA found the geographic coordinates for Taylor Airport needed to be adjusted to coincide with the FAA’s aeronautical database. This action makes the adjustment. Also, the airport names PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 have been changed: Taylor Municipal Airport to Taylor Airport, and Show Low Municipal Airport to Show Low Regional Airport. With the exception of editorial changes, and the changes described above, this rule is the same as that proposed in the NPRM. Class E airspace designations are published in paragraph 6005 of FAA Order 7400.9U dated August 18, 2010, and effective September 15, 2010, which is incorporated by reference in 14 CFR Part 71.1. The Class E airspace designations listed in this document will be published subsequently in that Order. The Rule This action amends Title 14 Code of Federal Regulations (14 CFR) Part 71 by modifying Class E airspace extending upward from 700 feet above the surface at Taylor Airport, Taylor, AZ, to accommodate IFR aircraft using the CAMBO One Departure, and the RNAV standard instrument approach procedures at the airport. This action is necessary for the safety and management of IFR operations. The geographic coordinates for Taylor Airport will be adjusted to coincide with the FAA’s aeronautical database. Also, Taylor Municipal Airport has been renamed Taylor Airport and Show Low Municipal Airport has been renamed Show Low Regional Airport. The FAA has determined this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Therefore, this regulation: (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) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified this rule, when promulgated, will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the U.S. Code. Subtitle 1, Section 106 discusses the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the agency’s authority. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use E:\FR\FM\04APR1.SGM 04APR1

Agencies

[Federal Register Volume 76, Number 64 (Monday, April 4, 2011)]
[Rules and Regulations]
[Pages 18376-18378]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-7729]


=======================================================================
-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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 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.

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 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: t.n.baktha@faa.gov.

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 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 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
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection of the elevator spar.....  8 work-hours x $85 per              N/A             $680         $525,640
                                       hour = $680.
----------------------------------------------------------------------------------------------------------------

    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: 
t.n.baktha@faa.gov. 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: 
t.n.baktha@faa.gov.

    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
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