81_FR_21571 81 FR 21501 - Airworthiness Directives; Textron Aviation Inc. Airplanes

81 FR 21501 - Airworthiness Directives; Textron Aviation Inc. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 70 (April 12, 2016)

Page Range21501-21503
FR Document2016-08259

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.

Federal Register, Volume 81 Issue 70 (Tuesday, April 12, 2016) 
[Federal Register Volume 81, Number 70 (Tuesday, April 12, 2016)]
[Proposed Rules]
[Pages 21501-21503]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-08259]


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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).

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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: 
[email protected].

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: [email protected].
    (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

Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules 21501 Commercial Airplanes Organization Notice of proposed rulemaking ACTION: Management Facility between 9 a.m. Designation Authorization (ODA) that has (NPRM). and 5 p.m., Monday through Friday, been authorized by the Manager, Seattle except Federal holidays. The AD docket ACO, to make those findings. To be SUMMARY: We propose to supersede contains this proposed AD, the approved, the repair method, modification Airworthiness Directive (AD) 2008–15– deviation, or alteration deviation must meet regulatory evaluation, any comments 06, which applies to certain Textron received, and other information. The the certification basis of the airplane, and the Aviation Inc. Models 175 and 175A approval must specifically refer to this AD. street address for the Docket Office airplanes (type certificate previously (phone: 800–647–5527) is in the (4) Except as required by paragraph (k)(2) of this AD: For service information that held by Cessna Aircraft Company). AD ADDRESSES section. Comments will be contains steps that are labeled as RC, the 2008–15–06 currently requires checking available in the AD docket shortly after provisions of paragraphs (m)(4)(i) and the airplane logbook to determine if the receipt. (m)(4)(ii) of this AD apply. original engine mounting brackets have been replaced. If the original engine FOR FURTHER INFORMATION CONTACT: Gary (i) The steps labeled as RC, including substeps under an RC step and any figures mounting brackets are still installed, the Park, Aerospace Engineer, Wichita identified in an RC step, must be done to AD requires repetitively inspecting Aircraft Certification Office, 1801 comply with the AD. An AMOC is required those brackets for cracks and replacing Airport Road, Room 100, Wichita, for any deviations to RC steps, including any cracked engine mounting bracket Kansas 67209; telephone: (316) 946– substeps and identified figures. 4123; fax: (316) 946–4107, email: (ii) Steps not labeled as RC may be until all four original engine mounting brackets are replaced. Replacing all four gary.park@faa.gov. deviated from using accepted methods in original engine mounting brackets SUPPLEMENTARY INFORMATION: accordance with the operator’s maintenance or inspection program without obtaining terminates the actions required in AD Comments Invited approval of an AMOC, provided the RC steps, 2008–15–06. Since we issued AD 2008– including substeps and identified figures, can 15–06, we have determined that the We invite you to send any written still be done as specified, and the airplane applicability needs to be changed to add relevant data, views, or arguments about can be put back in an airworthy condition. a serial number and take one out. This this proposed AD. Send your comments (n) Related Information proposed AD would retain the actions to an address listed under the required in AD 2008–15–06 and would ADDRESSES section. Include ‘‘Docket No. (1) For more information about this AD, FAA–2016–5579; Directorate Identifier contact Alan Pohl, Aerospace Engineer, change the Applicability section. We are Airframe Branch, ANM–120S, FAA, Seattle proposing this AD to correct the unsafe 2016–CE–010–AD’’ at the beginning of ACO, 1601 Lind Avenue SW., Renton, WA condition on these products. your comments. We specifically invite 98057–3356; phone: 425–917–6450; fax: 425– DATES: We must receive comments on comments on the overall regulatory, 917–6590; email: alan.pohl@faa.gov. this proposed AD by May 27, 2016. economic, environmental, and energy (2) For service information identified in aspects of this proposed AD. We will ADDRESSES: You may send comments, this AD, contact Boeing Commercial consider all comments received by the Airplanes, Attention: Data & Services using the procedures found in 14 CFR closing date and may amend this Management, P.O. Box 3707, MC 2H–65, 11.43 and 11.45, by any of the following proposed AD because of those Seattle, WA 98124–2207; telephone 206– methods: • Federal eRulemaking Portal: Go to comments. 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. For http://www.regulations.gov. Follow the We will post all comments we information on the availability of this instructions for submitting comments. receive, without change, to http:// material at the FAA, You may view this • Fax: 202–493–2251. www.regulations.gov, including any referenced service information at the FAA, • Mail: U.S. Department of personal information you provide. We Transport Airplane Directorate, 1601 Lind Transportation, Docket Operations, M– will also post a report summarizing each Avenue SW., Renton, WA. For information 30, West Building Ground Floor, Room substantive verbal contact we receive on the availability of this material at the about this proposed AD. FAA, call 425–227–1221. W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. Discussion Issued in Renton, Washington, on March • Hand Delivery: Deliver to Mail 31, 2016. address above between 9 a.m. and 5 On July 15, 2008, we issued AD 2008– Victor Wicklund, p.m., Monday through Friday, except 15–06, Amendment 39–15618 (73 FR Acting Manager, Transport Airplane Federal holidays. 43845, July 29, 2008), (‘‘AD 2008–15– Directorate, Aircraft Certification Service. For service information identified in 06’’), for certain Textron Aviation Inc. [FR Doc. 2016–08349 Filed 4–11–16; 8:45 am] this NPRM, contact Cessna Aircraft Models 175 and 175A airplanes (type BILLING CODE 4910–13–P Company, Product Support, P.O. Box certificate previously held by Cessna 7706, Wichita, Kansas 67277; telephone: Aircraft Company). AD 2008–15–06 (316) 517–5800; fax: (316) 942–9006; requires you to check the airplane DEPARTMENT OF TRANSPORTATION Internet: www.cessna.txtav.com. You logbook to determine if the original may review copies of the referenced engine mounting brackets have been Federal Aviation Administration service information at the FAA, Small replaced. If the original engine Airplane Directorate, 901 Locust, mounting brackets are still installed, 14 CFR Part 39 Kansas City, Missouri 64106. For this AD requires you to repetitively information on the availability of this inspect those brackets for cracks and [Docket No. FAA–2016–5579; Directorate replace any cracked engine mounting jstallworth on DSK7TPTVN1PROD with PROPOSALS material at the FAA, call (816) 329– Identifier 2016–CE–010–AD] bracket. After replacing all four original 4148. engine mounting brackets, no further RIN 2120–AA64 Examining the AD Docket action will be required by this AD. AD Airworthiness Directives; Textron You may examine the AD docket on 2008–15–06 resulted from a report of Aviation Inc. Airplanes the Internet at http:// the engine detaching from the firewall www.regulations.gov by searching for on a Cessna Model 175 airplane during AGENCY:Federal Aviation and locating Docket No. FAA–2016– landing. We issued AD 2008–15–06 to Administration (FAA), DOT. 5579; or in person at the Docket detect and correct cracks in the engine VerDate Sep<11>2014 15:12 Apr 11, 2016 Jkt 238001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\12APP1.SGM 12APP1

21502 Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules mounting brackets, which could result Related Service Information Under 1 and determined the unsafe condition in failure of the engine mounting CFR Part 51 described previously is likely to exist or bracket. This failure could lead to the We reviewed Cessna Single Engine develop in other products of the same engine detaching from the firewall. Service Bulletin SEB07–2, Revision 2, type design. Actions Since AD 2008–15–06 Was dated June 18, 2007. The service Proposed AD Requirements information describes procedures for Issued inspecting the upper and lower engine This proposed AD would retain the Since we issued AD 2008–15–06, we mounting brackets on both the left and requirements of AD 2008–15–06 and have determined that the applicability right sides for cracks and replacing would add a serial number to the for Model 175A airplanes needs to be cracked engine mounting brackets. This applicability and take one out. changed. We have determined that a service information is reasonably available because the interested parties Costs of Compliance serial number has been inadvertently have access to it through their normal included in the applicability and a We estimate that this AD would affect course of business or by the means serial number has been inadvertently 1,218 airplanes in the U.S. registry. identified in the ADDRESSES section. omitted from the applicability. We estimate the following costs to do FAA’s Determination each proposed inspection: We are proposing this AD because we evaluated all the relevant information Total cost per Total cost on Labor cost Parts cost airplane 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 brack- $200 per bracket. 4 × $200 = $800 $440 per bracket. $1,760 to re- ets per airplane × $240 per bracket = $960. for all 4 brackets. place all 4 brackets. There is no estimated cost of Regulatory Findings The Proposed Amendment compliance difference between this Accordingly, under the authority proposed AD and AD 2008–15–06 since We have determined that this proposed AD would not have federalism delegated to me by the Administrator, there is no change in the number of the FAA proposes to amend 14 CFR part affected airplanes or in the proposed implications under Executive Order 13132. This proposed AD would not 39 as follows: actions. The cost impact on the public would be in the removal of serial have a substantial direct effect on the PART 39—AIRWORTHINESS number 691 and the addition of serial States, on the relationship between the DIRECTIVES number 619. national Government and the States, or on the distribution of power and ■ 1. The authority citation for part 39 Authority for This Rulemaking responsibilities among the various continues to read as follows: Title 49 of the United States Code levels of government. specifies the FAA’s authority to issue Authority: 49 U.S.C. 106(g), 40113, 44701. For the reasons discussed above, I rules on aviation safety. Subtitle I, certify that the proposed regulation: § 39.13 [Amended] section 106, describes the authority of ■ 2. The FAA amends § 39.13 by the FAA Administrator. Subtitle VII, (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, removing Airworthiness Directive (AD) Aviation Programs, describes in more 2008–15–06, Amendment 39–15618 (73 detail the scope of the Agency’s (2) Is not a ‘‘significant rule’’ under FR 43845, July 29, 2008), and adding the authority. the DOT Regulatory Policies and following new AD: We are issuing this rulemaking under Procedures (44 FR 11034, February 26, the authority described in Subtitle VII, 1979), Textron Aviation Inc.: Docket No. FAA– Part A, Subpart III, section 44701, 2016–5579; Directorate Identifier 2016– (3) Will not affect intrastate aviation CE–010. ‘‘General requirements.’’ Under that in Alaska, and section, Congress charges the FAA with (a) Comments Due Date promoting safe flight of civil aircraft in (4) Will not have a significant The FAA must receive comments on this air commerce by prescribing regulations economic impact, positive or negative, AD action by May 27, 2016. jstallworth on DSK7TPTVN1PROD with PROPOSALS for practices, methods, and procedures on a substantial number of small entities under the criteria of the Regulatory (b) Affected ADs the Administrator finds necessary for safety in air commerce. This regulation Flexibility Act. This AD replaces AD 2008–15–06, is within the scope of that authority Amendment 39–15618 (73 FR 43845, July 29, List of Subjects in 14 CFR Part 39 2008) (‘‘AD 2008–15–06’’). because it addresses an unsafe condition that is likely to exist or develop on Air transportation, Aircraft, Aviation (c) Applicability products identified in this rulemaking safety, Incorporation by reference, This AD applies to the following Textron action. Safety. Aviation Inc. airplane models and serial VerDate Sep<11>2014 15:12 Apr 11, 2016 Jkt 238001 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 21503 numbers (type certificate previously held by (3) If you cannot positively determine that requested using the procedures found in 14 Cessna Aircraft Company) that are all four of the original engine mounting CFR 39.19. In accordance with 14 CFR 39.19, certificated in any category. brackets have been replaced, inspect each of send your request to your principal inspector (1) Airplanes previously affected by AD the upper and lower engine mounting or local Flight Standards District Office, as 2008–15–06 brackets on both the left and right sides for appropriate. If sending information directly cracks following Cessna Single Engine to the manager of the ACO, send it to the Year Service Bulletin SEB07–2, Revision 2, dated attention of the person identified in Model Serial Nos. June 18, 2007. Do the inspections at the paragraph (l) of this AD. manufactured following compliance times, as applicable. (2) Before using any approved AMOC, (1) 175 ......... 55001 1958. (i) For airplanes previous affected by AD notify your appropriate principal inspector, through 2008–15–06: Initially inspect within the next or lacking a principal inspector, the manager 55703. 12 months after September 2, 2008 (the of the local flight standards district office/ (2) 175 ......... 55704 1959. effective date retained from AD 2008–15–06). certificate holding district office. through If no cracks are found, repetitively inspect (3) AMOCs approved for AD 2008–15–06 56238. thereafter at intervals not to exceed 500 hours are approved as AMOCs for the (3) 175 ......... 28700A, 626, 1958 and time-in-service (TIS) until all four of the corresponding provisions of this AD. and 640. 1959. original engine mounting brackets are (l) Related Information (4) 175A ....... 56239 1960. replaced. through (ii) For the new airplane affected by this (1) For more information about this AD, 56777. AD: Initially inspect within the next 12 contact Gary Park, Aerospace Engineer, months after the effective date of this AD. If Wichita ACO, 1801 Airport Road, Room 100, no cracks are found, repetitively inspect Wichita, Kansas 67209; telephone: (316) 946– (2) New airplane affected by this AD: thereafter at intervals not to exceed 500 hours 4123; fax: (316) 946–4107, email: gary.park@ TIS until all four of the original engine faa.gov. Year (2) For service information identified in Model Serial Nos. mounting brackets are replaced. manufactured this AD, contact Cessna Aircraft Company, (h) Engine Mounting Bracket Replacement Product Support, P.O. Box 7706, Wichita, 175A ............. 619 1960. For all airplanes affected by this AD: If Kansas 67277; telephone: (316) 517–5800; cracks are found in any of the engine fax: (316) 942–9006; Internet: (d) Subject mounting brackets during any inspection www.cessna.txtav.com. You may view this Joint Aircraft System Component (JASC)/ required in paragraph (g)(3) of this AD, referenced service information at the FAA, Air Transport Association (ATA) of America including all subparagraphs, before further FAA, Small Airplane Directorate, 901 Locust, Code 71, Power Plant. flight after the inspection in which cracks are Kansas City, Missouri 64106. For information found, replace the cracked engine mounting on the availability of this material at the (e) Unsafe Condition bracket(s) following Cessna Single Engine FAA, call (816) 329–4148. This AD was prompted by the Service Bulletin SEB07–2, Revision 2, dated June 18, 2007. Replacing the cracked engine Issued in Kansas City, Missouri, on April determination that an airplane needs to be mounting bracket terminates the repetitive 4, 2016. added to the Applicability section and an airplane needs to be removed from the inspections required in paragraphs (g)(3)(i) Pat Mullen, Applicability section. We are issuing this AD and (g)(3)(ii) of this AD only for the replaced Acting Manager, Small Airplane Directorate, to detect and correct cracks in the engine engine mounting bracket. Aircraft Certification Service. mounting brackets, which could result in (i) Terminating Action [FR Doc. 2016–08259 Filed 4–11–16; 8:45 am] failure of the engine mounting bracket. This BILLING CODE 4910–13–P failure could lead to the engine detaching To terminate the repetitive inspections from the firewall. required in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD, you may replace all four original (f) Compliance engine mounting brackets following Cessna DEPARTMENT OF TRANSPORTATION Comply with this AD within the Single Engine Service Bulletin SEB07–2, compliance times specified, unless already Revision 2, dated June 18, 2007, at the Federal Aviation Administration done. following compliance times, as applicable. (1) For airplanes previous affected by AD 14 CFR Part 39 (g) Airplane Logbook Check 2008–15–06: At any time before or after the initial inspection required in paragraph [Docket No. FAA–2016–5463; Directorate (1) Check the airplane logbook to (g)(3)(i) of this AD. Identifier 2016–NM–013–AD] determine if all four of the original engine mounting brackets have been replaced. Do (2) For the new airplane affected by this RIN 2120–AA64 the logbook check at the following AD: At any time before or after the initial compliance time, as applicable. The owner/ inspection required in paragraph (g)(3)(ii) of Airworthiness Directives; Bombardier, operator holding at least a private pilot this AD. Inc. Airplanes certificate as authorized by section 43.7 may (j) Engine Mounting Bracket Disposal do this action. AGENCY: Federal Aviation For all airplanes affected by this AD: (i) For airplanes previously affected by AD Before further flight after the engine Administration (FAA), DOT. 2008–15–06: Within the next 30 days after ACTION: Notice of proposed rulemaking mounting bracket is removed for September 2, 2008 (the effective date retained replacement, dispose of every replaced (NPRM). from AD 2008–15–06). bracket following 14 CFR 43.10, paragraph (ii) For the new airplane affected by this (c)(6), which states the following: SUMMARY: We propose to adopt a new AD: Within the next 30 days after the ‘‘Mutilation. The part may be mutilated to airworthiness directive (AD) for certain effective date of this AD. deter its installation in a type certificated Bombardier, Inc. Model CL–600–2C10 jstallworth on DSK7TPTVN1PROD with PROPOSALS (2) If you can positively determine that all product. The mutilation must render the part (Regional Jet Series 700, 701, & 702), four of the original engine mounting brackets beyond repair and incapable of being have been replaced, no further action is Model CL–600–2D15 (Regional Jet reworked to appear to be airworthy.’’ Series 705), Model CL–600–2D24 required. Make an entry into the aircraft logbook showing compliance with this (k) Alternative Methods of Compliance (Regional Jet Series 900), and Model portion of the AD in accordance with 14 CFR (AMOCs) CL–600–2E25 (Regional Jet Series 1000) 43.9. The owner/operator holding at least a (1) The Manager, Wichita Aircraft airplanes. This proposed AD was private pilot certificate as authorized by Certification Office (ACO), FAA, has the prompted by reports of corrosion found section 43.7 may do this action. authority to approve AMOCs for this AD, if on the slat and flap torque tubes in the VerDate Sep<11>2014 15:12 Apr 11, 2016 Jkt 238001 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 E:\FR\FM\12APP1.SGM 12APP1


Document Created: 2016-04-12 00:47:16
Document Modified: 2016-04-12 00:47:16
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by May 27, 2016.
ContactGary Park, Aerospace Engineer, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-4107, email: [email protected]
FR Citation81 FR 21501 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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