
[Federal Register Volume 82, Number 69 (Wednesday, April 12, 2017)]
[Proposed Rules]
[Pages 17594-17597]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-07343]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0288; Directorate Identifier 2017-CE-007-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 adopt a new airworthiness directive (AD) for all 
Textron Aviation Inc. Models A36TC and B36TC airplanes. This proposed 
AD was prompted by a fatal accident where the exhaust tailpipe fell off 
during takeoff. This proposed AD would add a life limit to the exhaust 
tailpipe v-band coupling (clamp) that attaches the

[[Page 17595]]

exhaust tailpipe to the turbocharger and, if the coupling is removed 
for any reason before the life limit is reached, this proposed AD would 
require an inspection of the coupling before reinstalling. We are 
proposing this AD to correct the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by May 30, 2017.

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.

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-2017-
0288; 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: Thomas Teplik, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 
100, Wichita, Kansas 67209; phone: (316) 946-4196; fax: (316) 946-4107; 
email: thomas.teplik@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0288; 
Directorate Identifier 2017-CE-007-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

    We were notified of a fatal accident involving a Textron Aviation 
Inc. (Beech Bonanza) Model A36TC airplane. The National Transportation 
Safety Board preliminary report stated that shortly after takeoff the 
pilot advised the control tower that there was smoke in the cockpit and 
they needed to return to the airport. Witnesses reported seeing smoke 
and flames coming from the airplane before it impacted terrain. The 
exhaust tailpipe, a fractured v-band coupling (clamp) that attached the 
exhaust tailpipe to the turbocharger, and small fragments of fabric 
insulation were recovered from the runway. Failure of the exhaust 
tailpipe v-band coupling may lead to detachment of the exhaust tailpipe 
from the turbocharger and allow high-temperature exhaust gases to enter 
the engine compartment, which could result in an inflight fire.

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 add a life limit to the exhaust tailpipe v-
band coupling and, if the coupling is removed for any reason before the 
life limit is reached, this AD would require an inspection of the v-
band coupling before reinstalling.

Costs of Compliance

    We estimate that this proposed AD affects 499 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
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Replacement of the exhaust tailpipe v-  2 work-hours x $85 per              $300            $470        $234,530
 band coupling (clamp).                  hour = $170.
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    We estimate the following costs to do any necessary inspection that 
would be required based on removal and reinstallation of the exhaust 
tailpipe v-band coupling. We have no way of determining the number of 
airplanes that might need this inspection:

                                               On-Condition Costs
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                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Inspection of the exhaust tailpipe v-band       1 work-hour x $85 per hour = $85  Not applicable             $85
 coupling (clamp).
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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,

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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 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 this 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 adding the following new airworthiness 
directive (AD):

Textron Aviation Inc.: Docket No. FAA-2017-0288; Directorate 
Identifier 2017-CE-007-AD

(a) Comments Due Date

    We must receive comments by May 30, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Textron Aviation Inc. Models A36TC and B36TC 
airplanes; all serial numbers, that are certificated in any 
category.

 (d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 81, Turbocharging.

(e) Unsafe Condition

    This AD was prompted by a fatal accident where the exhaust 
tailpipe fell off during takeoff. We are issuing this AD to prevent 
failure of the exhaust tailpipe v-band coupling that may lead to 
detachment of the exhaust tailpipe from the turbocharger and allow 
high-temperature exhaust gases to enter the engine compartment, 
which could result in an inflight fire.

(f) Compliance

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

(g) Replacement of the V-Band Coupling (Clamp)

    Replace the exhaust tailpipe v-band coupling part number (P/N) 
N4211-375-M or P/N 5322C-375-Z (P/Ns are also known as P/N N4211-
375M and P/N 5322C3752) with a new exhaust tailpipe v-band coupling. 
When installing the new part, tighten the v-band coupling to 40 in-
lbs., tap the periphery of the band to distribute tension, and 
torque again to 40 in-lbs. Do the replacement at the compliance 
times in paragraphs (g)(1) and (2) of this AD. For the purposes of 
this AD, the exhaust tailpipe v-band coupling may also be referred 
to as the exhaust tailpipe v-band clamp.

    Note 1 to paragraph (g) of this AD: The engineering drawing 
lists the applicable part number v-band couplings as P/N N4211-375-M 
and P/N 5322C-375-Z; however, the parts catalog lists the applicable 
v-band couplings as P/N N4211-375M and P/N 5322C3752.


    Note 2 to paragraphs (g) and (h)(2) of this AD: We recommend 
after installation of the exhaust tailpipe v-band coupling, you do 
an engine run and recheck the torque of the v-band coupling.

    (1) If from a review of the maintenance records you can 
positively identify that the hours time-in-service (TIS) for the 
exhaust tailpipe v-band coupling is less than 500 hours TIS: Do the 
initial replacement within 500 hours TIS for the exhaust tailpipe v-
band coupling or within the next 50 hours TIS after the effective 
date of this AD, whichever occurs later, and replace repetitively 
thereafter at intervals not to exceed 500 hours TIS on the exhaust 
tailpipe v-band coupling.
    (2) If from a review of the maintenance records you can 
positively identify that the hours TIS for the exhaust tailpipe v-
band coupling is 500 hours TIS or more or you cannot positively 
identify the hours TIS for the exhaust tailpipe v-band coupling: Do 
the initial replacement within 50 hours TIS after the effective date 
of this AD and replace repetitively thereafter at intervals not to 
exceed 500 hours TIS on the exhaust tailpipe v-band coupling.

(h) Removal of the Exhaust Tailpipe V-Band Coupling Before Reaching the 
500-Hour Life Limit

    (1) If the exhaust tailpipe v-band coupling is removed for any 
reason before any replacement required by this AD, before re-
installing the same (existing) v-band coupling, you must do the 
inspection steps listed in paragraphs (h)(1)(i) through (vi) of this 
AD. During the removal, inspection, and reinstallation do not open 
the coupling more than necessary because excessive flexing of the 
coupling can lead to damage.
    (i) Use crocus cloth and mineral spirits/Stoddard solvent, to 
clean the outer band of the v-band coupling. Pay particular 
attention to the spot weld areas on the coupling.
    (ii) Use a 10X magnifier to visually inspect the outer band for 
cracks, paying particular attention to the spot weld areas. If 
cracks are found during this inspection, do not re-install the v-
band coupling. Before further flight, you must install a new v-band 
coupling and restart the hours TIS for the repetitive replacement of 
the v-band coupling.
    (iii) Visually inspect the flatness of the outer band using a 
straight edge. Lay the straight edge across the width of the outer 
band. The gap must be less than 0.062 inches. See figure 1 to 
paragraphs (h)(1)(iii) and (v) of this AD. If the gap exceeds 0.062 
inches between the outer band and the straight edge, do not re-
install the v-band coupling. Before further flight, you must install 
a new v-band coupling and restart the hours TIS for the repetitive 
replacement of the v-band coupling.
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[GRAPHIC] [TIFF OMITTED] TP12AP17.000

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    (iv) With the t-bolt in the 12 o'clock position, visually 
inspect the coupling for the attachment of the outer band to the v-
retainer coupling segments by inspecting for gaps between the outer 
band and the v-retainer coupling segments between approximately the 
1 o'clock through 11 o'clock position. It is recommended to use 
backlighting to see gaps. If gaps between the outer band and the v-
retainer coupling segments are found, do not re-install the v-band 
coupling. Before further flight, you must install a new v-band 
coupling and restart the hours TIS for the repetitive replacement of 
the v-band coupling.
    (v) Visually inspect the bend radii of the coupling v-retainer 
coupling segments for cracks. Inspect the radii throughout the 
length of the segment. See figure 1 to paragraphs (h)(1)(iii) and 
(v) of this AD. If any cracks are found, do not re-install the v-
band coupling. Before further flight, you must install a new v-band 
coupling and restart the hours TIS for the repetitive replacement of 
the v-band coupling.
    (vi) Visually inspect the outer band opposite the t-bolt for 
damage (distortion, creases, bulging, or cracks), which may be 
caused from excessive spreading of the coupling during installation 
and/or removal. If any damage is found, do not re-install the v-band 
coupling. Before further flight, you must install a new v-band 
coupling and restart the hours TIS for the repetitive replacement of 
the v-band coupling.
    (2) If the removed exhaust tailpipe v-band coupling passes all 
of the inspection steps listed in paragraphs (h)(1)(i) through (vi) 
of this AD, you may re-install the same v-band coupling. After the 
coupling is re-installed and torqued as specified in paragraph (g) 
of this AD, verify there is space between each v-retainer coupling 
segment below the t-bolt. If there is no space between each v-
retainer coupling segment below the t-bolt, before further flight, 
you must install a new v-band coupling and restart the hours TIS for 
the repetitive replacement of the v-band coupling.
    (3) The inspections required in paragraphs (h)(1) and (2) of 
this AD only apply to re-installing the same exhaust tailpipe v-band 
coupling that was removed for any reason as specified in paragraph 
(h)(1) of this AD. It does not apply to installation of a new v-band 
coupling. These inspections do not terminate the 500-hour TIS 
repetitive replacement of the v-band coupling and do not restart the 
hours TIS for the repetitive replacement of the v-band coupling.
    (4) After the effective date of this AD, do not install a used 
exhaust tailpipe v-band coupling on the airplane except for the 
reinstallation of the inspected exhaust tailpipe v-band coupling 
that was removed for any reason as specified in paragraph (h)(1) of 
this AD.

(i) 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 (j) 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.

(j) Related Information

    For more information about this AD, contact Thomas Teplik, 
Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; phone: (316) 946-4196; fax: (316) 946-4107; 
email: thomas.teplik@faa.gov.

    Issued in Kansas City, Missouri, on April 3, 2017.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-07343 Filed 4-11-17; 8:45 am]
 BILLING CODE 4910-13-P


