Airworthiness Directives; Textron Aviation Inc. Airplanes, 21501-21503 [2016-08259]

Download as PDF Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (k)(2) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (m)(4)(i) and (m)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (n) Related Information (1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6450; fax: 425– 917–6590; email: alan.pohl@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. For information on the availability of this material at the FAA, You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on March 31, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–08349 Filed 4–11–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration jstallworth on DSK7TPTVN1PROD with PROPOSALS 14 CFR Part 39 [Docket No. FAA–2016–5579; Directorate Identifier 2016–CE–010–AD] RIN 2120–AA64 Airworthiness Directives; Textron Aviation Inc. Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Sep<11>2014 15:12 Apr 11, 2016 Jkt 238001 Notice of proposed rulemaking (NPRM). ACTION: We propose to supersede Airworthiness Directive (AD) 2008–15– 06, which applies to certain Textron Aviation Inc. Models 175 and 175A airplanes (type certificate previously held by Cessna Aircraft Company). AD 2008–15–06 currently requires checking the airplane logbook to determine if the original engine mounting brackets have been replaced. If the original engine mounting brackets are still installed, the AD requires repetitively inspecting those brackets for cracks and replacing any cracked engine mounting bracket until all four original engine mounting brackets are replaced. Replacing all four original engine mounting brackets terminates the actions required in AD 2008–15–06. Since we issued AD 2008– 15–06, we have determined that the applicability needs to be changed to add a serial number and take one out. This proposed AD would retain the actions required in AD 2008–15–06 and would change the Applicability section. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by May 27, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517–5800; fax: (316) 942–9006; Internet: www.cessna.txtav.com. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5579; or in person at the Docket PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 21501 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 (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4123; fax: (316) 946–4107, email: gary.park@faa.gov. 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–2016–5579; Directorate Identifier 2016–CE–010–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 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 proposed AD. Discussion On July 15, 2008, we issued AD 2008– 15–06, Amendment 39–15618 (73 FR 43845, July 29, 2008), (‘‘AD 2008–15– 06’’), for certain Textron Aviation Inc. Models 175 and 175A airplanes (type certificate previously held by Cessna Aircraft Company). AD 2008–15–06 requires you to check the airplane logbook to determine if the original engine mounting brackets have been replaced. If the original engine mounting brackets are still installed, this AD requires you to repetitively inspect those brackets for cracks and replace any cracked engine mounting bracket. After replacing all four original engine mounting brackets, no further action will be required by this AD. AD 2008–15–06 resulted from a report of the engine detaching from the firewall on a Cessna Model 175 airplane during landing. We issued AD 2008–15–06 to detect and correct cracks in the engine E:\FR\FM\12APP1.SGM 12APP1 21502 Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules mounting brackets, which could result in failure of the engine mounting bracket. This failure could lead to the engine detaching from the firewall. Actions Since AD 2008–15–06 Was Issued Since we issued AD 2008–15–06, we have determined that the applicability for Model 175A airplanes needs to be changed. We have determined that a serial number has been inadvertently included in the applicability and a serial number has been inadvertently omitted from the applicability. Related Service Information Under 1 CFR Part 51 We reviewed Cessna Single Engine Service Bulletin SEB07–2, Revision 2, dated June 18, 2007. The service information describes procedures for inspecting the upper and lower engine mounting brackets on both the left and right sides for cracks and replacing cracked engine mounting brackets. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing 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. Proposed AD Requirements This proposed AD would retain the requirements of AD 2008–15–06 and would add a serial number to the applicability and take one out. Costs of Compliance We estimate that this AD would affect 1,218 airplanes in the U.S. registry. We estimate the following costs to do each proposed inspection: Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 7.5 work-hours × $80 per hour = $600 ........................ Not applicable ............................................................... $600 $730,800 We estimate the following costs to do any necessary proposed replacements: Labor cost Parts cost Total cost per airplane 3 work-hours per bracket × $80 per hour = $240 per bracket. 4 brackets per airplane × $240 per bracket = $960. $200 per bracket. 4 × $200 = $800 for all 4 brackets. $440 per bracket. $1,760 to replace all 4 brackets. jstallworth on DSK7TPTVN1PROD with PROPOSALS There is no estimated cost of compliance difference between this proposed AD and AD 2008–15–06 since there is no change in the number of affected airplanes or in the proposed actions. The cost impact on the public would be in the removal of serial number 691 and the addition of serial number 619. 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. VerDate Sep<11>2014 15:12 Apr 11, 2016 Jkt 238001 Regulatory Findings The Proposed Amendment 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), (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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 removing Airworthiness Directive (AD) 2008–15–06, Amendment 39–15618 (73 FR 43845, July 29, 2008), and adding the following new AD: ■ Textron Aviation Inc.: Docket No. FAA– 2016–5579; Directorate Identifier 2016– CE–010. (a) Comments Due Date The FAA must receive comments on this AD action by May 27, 2016. List of Subjects in 14 CFR Part 39 (b) Affected ADs This AD replaces AD 2008–15–06, Amendment 39–15618 (73 FR 43845, July 29, 2008) (‘‘AD 2008–15–06’’). Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (c) Applicability This AD applies to the following Textron Aviation Inc. airplane models and serial PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 E:\FR\FM\12APP1.SGM 12APP1 Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules numbers (type certificate previously held by Cessna Aircraft Company) that are certificated in any category. (1) Airplanes previously affected by AD 2008–15–06 Model Serial Nos. (1) 175 ......... 55001 through 55703. 55704 through 56238. 28700A, 626, and 640. 56239 through 56777. (2) 175 ......... (3) 175 ......... (4) 175A ....... Year manufactured 1958. 1959. 1958 and 1959. 1960. (2) New airplane affected by this AD: Model Serial Nos. 175A ............. 619 Year manufactured 1960. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 71, Power Plant. (e) Unsafe Condition This AD was prompted by the determination that an airplane needs to be added to the Applicability section and an airplane needs to be removed from the Applicability section. We are issuing this AD to detect and correct cracks in the engine mounting brackets, which could result in failure of the engine mounting bracket. This failure could lead to the engine detaching from the firewall. (f) Compliance Comply with this AD within the compliance times specified, unless already done. jstallworth on DSK7TPTVN1PROD with PROPOSALS (g) Airplane Logbook Check (1) Check the airplane logbook to determine if all four of the original engine mounting brackets have been replaced. Do the logbook check at the following compliance time, as applicable. The owner/ operator holding at least a private pilot certificate as authorized by section 43.7 may do this action. (i) For airplanes previously affected by AD 2008–15–06: Within the next 30 days after September 2, 2008 (the effective date retained from AD 2008–15–06). (ii) For the new airplane affected by this AD: Within the next 30 days after the effective date of this AD. (2) If you can positively determine that all four of the original engine mounting brackets have been replaced, no further action is required. Make an entry into the aircraft logbook showing compliance with this portion of the AD in accordance with 14 CFR 43.9. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 may do this action. VerDate Sep<11>2014 15:12 Apr 11, 2016 Jkt 238001 (3) If you cannot positively determine that all four of the original engine mounting brackets have been replaced, inspect each of the upper and lower engine mounting brackets on both the left and right sides for cracks following Cessna Single Engine Service Bulletin SEB07–2, Revision 2, dated June 18, 2007. Do the inspections at the following compliance times, as applicable. (i) For airplanes previous affected by AD 2008–15–06: Initially inspect within the next 12 months after September 2, 2008 (the effective date retained from AD 2008–15–06). If no cracks are found, repetitively inspect thereafter at intervals not to exceed 500 hours time-in-service (TIS) until all four of the original engine mounting brackets are replaced. (ii) For the new airplane affected by this AD: Initially inspect within the next 12 months after the effective date of this AD. If no cracks are found, repetitively inspect thereafter at intervals not to exceed 500 hours TIS until all four of the original engine mounting brackets are replaced. (h) Engine Mounting Bracket Replacement For all airplanes affected by this AD: If cracks are found in any of the engine mounting brackets during any inspection required in paragraph (g)(3) of this AD, including all subparagraphs, before further flight after the inspection in which cracks are found, replace the cracked engine mounting bracket(s) following Cessna Single Engine Service Bulletin SEB07–2, Revision 2, dated June 18, 2007. Replacing the cracked engine mounting bracket terminates the repetitive inspections required in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD only for the replaced engine mounting bracket. (i) Terminating Action To terminate the repetitive inspections required in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD, you may replace all four original engine mounting brackets following Cessna Single Engine Service Bulletin SEB07–2, Revision 2, dated June 18, 2007, at the following compliance times, as applicable. (1) For airplanes previous affected by AD 2008–15–06: At any time before or after the initial inspection required in paragraph (g)(3)(i) of this AD. (2) For the new airplane affected by this AD: At any time before or after the initial inspection required in paragraph (g)(3)(ii) of this AD. (j) Engine Mounting Bracket Disposal For all airplanes affected by this AD: Before further flight after the engine mounting bracket is removed for replacement, dispose of every replaced bracket following 14 CFR 43.10, paragraph (c)(6), which states the following: ‘‘Mutilation. The part may be mutilated to deter its installation in a type certificated product. The mutilation must render the part beyond repair and incapable of being reworked to appear to be airworthy.’’ (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 21503 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 paragraph (l) 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. (3) AMOCs approved for AD 2008–15–06 are approved as AMOCs for the corresponding provisions of this AD. (l) Related Information (1) For more information about this AD, contact Gary Park, Aerospace Engineer, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4123; fax: (316) 946–4107, email: gary.park@ faa.gov. (2) For service information identified in this AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517–5800; fax: (316) 942–9006; Internet: www.cessna.txtav.com. You may view this referenced service information at the FAA, FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued in Kansas City, Missouri, on April 4, 2016. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–08259 Filed 4–11–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5463; Directorate Identifier 2016–NM–013–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2C10 (Regional Jet Series 700, 701, & 702), Model CL–600–2D15 (Regional Jet Series 705), Model CL–600–2D24 (Regional Jet Series 900), and Model CL–600–2E25 (Regional Jet Series 1000) airplanes. This proposed AD was prompted by reports of corrosion found on the slat and flap torque tubes in the SUMMARY: E:\FR\FM\12APP1.SGM 12APP1

Agencies

[Federal Register Volume 81, Number 70 (Tuesday, April 12, 2016)]
[Proposed Rules]
[Pages 21501-21503]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08259]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5579; Directorate Identifier 2016-CE-010-AD]
RIN 2120-AA64


Airworthiness Directives; Textron Aviation Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2008-15-
06, which applies to certain Textron Aviation Inc. Models 175 and 175A 
airplanes (type certificate previously held by Cessna Aircraft 
Company). AD 2008-15-06 currently requires checking the airplane 
logbook to determine if the original engine mounting brackets have been 
replaced. If the original engine mounting brackets are still installed, 
the AD requires repetitively inspecting those brackets for cracks and 
replacing any cracked engine mounting bracket until all four original 
engine mounting brackets are replaced. Replacing all four original 
engine mounting brackets terminates the actions required in AD 2008-15-
06. Since we issued AD 2008-15-06, we have determined that the 
applicability needs to be changed to add a serial number and take one 
out. This proposed AD would retain the actions required in AD 2008-15-
06 and would change the Applicability section. We are proposing this AD 
to correct the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by May 27, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Cessna 
Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 
67277; telephone: (316) 517-5800; fax: (316) 942-9006; Internet: 
www.cessna.txtav.com. You may review copies of the referenced service 
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas 
City, Missouri 64106. For information on the availability of this 
material at the FAA, call (816) 329-4148.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5579; 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 (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita 
Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, 
Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-4107, email: 
gary.park@faa.gov.

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-2016-5579; 
Directorate Identifier 2016-CE-010-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 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 proposed AD.

Discussion

    On July 15, 2008, we issued AD 2008-15-06, Amendment 39-15618 (73 
FR 43845, July 29, 2008), (``AD 2008-15-06''), for certain Textron 
Aviation Inc. Models 175 and 175A airplanes (type certificate 
previously held by Cessna Aircraft Company). AD 2008-15-06 requires you 
to check the airplane logbook to determine if the original engine 
mounting brackets have been replaced. If the original engine mounting 
brackets are still installed, this AD requires you to repetitively 
inspect those brackets for cracks and replace any cracked engine 
mounting bracket. After replacing all four original engine mounting 
brackets, no further action will be required by this AD. AD 2008-15-06 
resulted from a report of the engine detaching from the firewall on a 
Cessna Model 175 airplane during landing. We issued AD 2008-15-06 to 
detect and correct cracks in the engine

[[Page 21502]]

mounting brackets, which could result in failure of the engine mounting 
bracket. This failure could lead to the engine detaching from the 
firewall.

Actions Since AD 2008-15-06 Was Issued

    Since we issued AD 2008-15-06, we have determined that the 
applicability for Model 175A airplanes needs to be changed. We have 
determined that a serial number has been inadvertently included in the 
applicability and a serial number has been inadvertently omitted from 
the applicability.

Related Service Information Under 1 CFR Part 51

    We reviewed Cessna Single Engine Service Bulletin SEB07-2, Revision 
2, dated June 18, 2007. The service information describes procedures 
for inspecting the upper and lower engine mounting brackets on both the 
left and right sides for cracks and replacing cracked engine mounting 
brackets. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination

    We are proposing 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.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 2008-15-06 and 
would add a serial number to the applicability and take one out.

Costs of Compliance

    We estimate that this AD would affect 1,218 airplanes in the U.S. 
registry.
    We estimate the following costs to do each proposed inspection:

----------------------------------------------------------------------------------------------------------------
                                                                                 Total cost per   Total cost on
                  Labor cost                              Parts cost                airplane      U.S. operators
----------------------------------------------------------------------------------------------------------------
7.5 work-hours x $80 per hour = $600.........  Not applicable.................            $600         $730,800
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary proposed 
replacements:

------------------------------------------------------------------------
                                                        Total cost per
           Labor cost                 Parts cost           airplane
------------------------------------------------------------------------
3 work-hours per bracket x $80    $200 per bracket.   $440 per bracket.
 per hour = $240 per bracket. 4    4 x $200 = $800     $1,760 to replace
 brackets per airplane x $240      for all 4           all 4 brackets.
 per bracket = $960.               brackets.
------------------------------------------------------------------------

    There is no estimated cost of compliance difference between this 
proposed AD and AD 2008-15-06 since there is no change in the number of 
affected airplanes or in the proposed actions. The cost impact on the 
public would be in the removal of serial number 691 and the addition of 
serial number 619.

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),
    (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, 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:

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 removing Airworthiness Directive (AD) 
2008-15-06, Amendment 39-15618 (73 FR 43845, July 29, 2008), and adding 
the following new AD:

Textron Aviation Inc.: Docket No. FAA-2016-5579; Directorate 
Identifier 2016-CE-010.

(a) Comments Due Date

    The FAA must receive comments on this AD action by May 27, 2016.

(b) Affected ADs

    This AD replaces AD 2008-15-06, Amendment 39-15618 (73 FR 43845, 
July 29, 2008) (``AD 2008-15-06'').

(c) Applicability

    This AD applies to the following Textron Aviation Inc. airplane 
models and serial

[[Page 21503]]

numbers (type certificate previously held by Cessna Aircraft 
Company) that are certificated in any category.
    (1) Airplanes previously affected by AD 2008-15-06

------------------------------------------------------------------------
             Model                   Serial Nos.      Year manufactured
------------------------------------------------------------------------
(1) 175........................  55001 through       1958.
                                  55703.
(2) 175........................  55704 through       1959.
                                  56238.
(3) 175........................  28700A, 626, and    1958 and 1959.
                                  640.
(4) 175A.......................  56239 through       1960.
                                  56777.
------------------------------------------------------------------------

    (2) New airplane affected by this AD:

------------------------------------------------------------------------
                                                               Year
                   Model                     Serial Nos.   manufactured
------------------------------------------------------------------------
175A.......................................          619           1960.
------------------------------------------------------------------------

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 71, Power Plant.

(e) Unsafe Condition

    This AD was prompted by the determination that an airplane needs 
to be added to the Applicability section and an airplane needs to be 
removed from the Applicability section. We are issuing this AD to 
detect and correct cracks in the engine mounting brackets, which 
could result in failure of the engine mounting bracket. This failure 
could lead to the engine detaching from the firewall.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Airplane Logbook Check

    (1) Check the airplane logbook to determine if all four of the 
original engine mounting brackets have been replaced. Do the logbook 
check at the following compliance time, as applicable. The owner/
operator holding at least a private pilot certificate as authorized 
by section 43.7 may do this action.
    (i) For airplanes previously affected by AD 2008-15-06: Within 
the next 30 days after September 2, 2008 (the effective date 
retained from AD 2008-15-06).
    (ii) For the new airplane affected by this AD: Within the next 
30 days after the effective date of this AD.
    (2) If you can positively determine that all four of the 
original engine mounting brackets have been replaced, no further 
action is required. Make an entry into the aircraft logbook showing 
compliance with this portion of the AD in accordance with 14 CFR 
43.9. The owner/operator holding at least a private pilot 
certificate as authorized by section 43.7 may do this action.
    (3) If you cannot positively determine that all four of the 
original engine mounting brackets have been replaced, inspect each 
of the upper and lower engine mounting brackets on both the left and 
right sides for cracks following Cessna Single Engine Service 
Bulletin SEB07-2, Revision 2, dated June 18, 2007. Do the 
inspections at the following compliance times, as applicable.
    (i) For airplanes previous affected by AD 2008-15-06: Initially 
inspect within the next 12 months after September 2, 2008 (the 
effective date retained from AD 2008-15-06). If no cracks are found, 
repetitively inspect thereafter at intervals not to exceed 500 hours 
time-in-service (TIS) until all four of the original engine mounting 
brackets are replaced.
    (ii) For the new airplane affected by this AD: Initially inspect 
within the next 12 months after the effective date of this AD. If no 
cracks are found, repetitively inspect thereafter at intervals not 
to exceed 500 hours TIS until all four of the original engine 
mounting brackets are replaced.

(h) Engine Mounting Bracket Replacement

    For all airplanes affected by this AD: If cracks are found in 
any of the engine mounting brackets during any inspection required 
in paragraph (g)(3) of this AD, including all subparagraphs, before 
further flight after the inspection in which cracks are found, 
replace the cracked engine mounting bracket(s) following Cessna 
Single Engine Service Bulletin SEB07-2, Revision 2, dated June 18, 
2007. Replacing the cracked engine mounting bracket terminates the 
repetitive inspections required in paragraphs (g)(3)(i) and 
(g)(3)(ii) of this AD only for the replaced engine mounting bracket.

(i) Terminating Action

    To terminate the repetitive inspections required in paragraphs 
(g)(3)(i) and (g)(3)(ii) of this AD, you may replace all four 
original engine mounting brackets following Cessna Single Engine 
Service Bulletin SEB07-2, Revision 2, dated June 18, 2007, at the 
following compliance times, as applicable.
    (1) For airplanes previous affected by AD 2008-15-06: At any 
time before or after the initial inspection required in paragraph 
(g)(3)(i) of this AD.
    (2) For the new airplane affected by this AD: At any time before 
or after the initial inspection required in paragraph (g)(3)(ii) of 
this AD.

(j) Engine Mounting Bracket Disposal

    For all airplanes affected by this AD: Before further flight 
after the engine mounting bracket is removed for replacement, 
dispose of every replaced bracket following 14 CFR 43.10, paragraph 
(c)(6), which states the following: ``Mutilation. The part may be 
mutilated to deter its installation in a type certificated product. 
The mutilation must render the part beyond repair and incapable of 
being reworked to appear to be airworthy.''

(k) Alternative Methods of Compliance (AMOCs)

    (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. 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 paragraph (l) 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.
    (3) AMOCs approved for AD 2008-15-06 are approved as AMOCs for 
the corresponding provisions of this AD.

(l) Related Information

    (1) For more information about this AD, contact Gary Park, 
Aerospace Engineer, Wichita ACO, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-
4107, email: gary.park@faa.gov.
    (2) For service information identified in this AD, contact 
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, 
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006; 
Internet: www.cessna.txtav.com. You may view this referenced service 
information at the FAA, FAA, Small Airplane Directorate, 901 Locust, 
Kansas City, Missouri 64106. For information on the availability of 
this material at the FAA, call (816) 329-4148.

    Issued in Kansas City, Missouri, on April 4, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08259 Filed 4-11-16; 8:45 am]
 BILLING CODE 4910-13-P