Document ID: FAA-2016-3705-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Textron Aviation Inc. (Type Certificate Previously Held by Cessna Aircraft Company) Airplanes
Posted Date: 2016-02-26T05:00Z

[Federal Register Volume 81, Number 38 (Friday, February 26, 2016)]
[Proposed Rules]
[Pages 9790-9793]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04136]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3705; Directorate Identifier 2015-NM-168-AD]
RIN 2120-AA64

Airworthiness Directives; Textron Aviation Inc. (Type Certificate 
Previously Held by Cessna Aircraft Company) Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 9791]]

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Textron Aviation Inc. Model 680 airplanes. This proposed AD was 
prompted by Cessna's report of a manufacturing defect which affects the 
durability of the aft canted bulkhead metallic structure. The 
manufacturing defect directly affects the bond integrity of the 
vertical and horizontal stiffeners on the aft canted bulkhead metallic 
structure. This proposed AD would require repetitive inspections of the 
aft canted bulkhead, and repair if necessary. This proposed AD would 
also require a modification, which would terminate the repetitive 
inspections. We are proposing this AD to prevent disbonding of the 
horizontal and vertical stiffeners on the aft canted bulkhead. Loss of 
bond integrity could result in a structural failure that could lead to 
separation of the cruciform tail and loss of control of the airplane.

DATES: We must receive comments on this proposed AD by April 11, 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 Textron 
Aviation Inc., P.O. Box 7706, Wichita, KS 67277; telephone 316-517-
6215; fax 316-517-5802; email citationpubs@txtav.com; Internet https://support.cessna.com/custsupt/csupport/newlogin.jsp. You may review 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.

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-
3705; 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: Paul Kalowski, Aerospace Engineer, 
Airframe Branch, ACE-118W, Wichita Aircraft Certification Office (ACO), 
FAA, 1801 Airport Road, Room 100, Dwight D. Eisenhower Airport, 
Wichita, KS 67209; phone: 316-946-4186; fax: 316-946-4107; email: 
paul.kalowski@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-2016-3705; 
Directorate Identifier 2015-NM-168-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

    This proposed AD was prompted by Cessna's report of a manufacturing 
defect that affects the durability of the aft canted bulkhead metallic 
structure. The manufacturing defect directly affects the bond integrity 
of the vertical and horizontal stiffeners on the aft canted bulkhead 
metallic structure. This disbonding is caused by a loss of durability 
in the metal-to-metal bondline, which resulted from a reduced autoclave 
cure cycle dwell time and temperature during manufacturing. This 
condition, if not detected and corrected, could result in a structural 
failure that could lead to separation of the cruciform tail and loss of 
control of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Cessna service information.
     Cessna Service Letter SL680-53-05, Revision 2, dated 
September 30, 2015. The service information describes procedures for a 
general visual inspection for disbonding and paint cracking around the 
edges of the stiffeners on the aft canted bulkhead.
     Cessna Service Bulletin SB680-53-08, dated September 28, 
2015. The service information describes procedures for modifying the 
airplane by installing additional stiffeners to the aft canted 
bulkhead.
    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 require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.''

Differences Between This Proposed AD and the Service Information

    Although Cessna Service Letter SL680-53-05, Revision 2, dated 
September 30, 2015, specifies reporting the inspection results to 
Cessna, this proposed AD would not require those actions.
    Although Cessna Service Letter SL680-53-05, Revision 2, dated 
September 30, 2015, specifies that operators may contact the 
manufacturer for disposition of certain conditions, this proposed AD 
would require operators to repair those conditions in accordance with a 
method approved by the FAA.
    Although Cessna Service Letter SL680-53-05, Revision 2, dated 
September 30, 2015; and Service Bulletin SB680-53-08, dated September 
28, 2015; use the term ``debond'' to describe full or partial 
separation of a stiffener from the aft canted bulkhead structure, this 
proposed AD instead uses the term ``disbond.''

Costs of Compliance

    We estimate that this proposed AD affects 123 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 9792]]

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  1 work-hour x $85 per                $0  $85 per inspection  $10,455 per
                                  hour = $85 per                           cycle.              inspection cycle.
                                  inspection cycle.
Modification...................  180 work-hours x $85              3,190  $18,490...........  $2,274,270.
                                  per hour = $15,300.
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    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 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. (Type Certificate Previously Held by Cessna 
Aircraft Company): Docket No. FAA-2016-3705; Directorate Identifier 
2015-NM-168-AD.--

(a) Comments Due Date

    We must receive comments by April 11, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Textron Aviation Inc. (Type Certificate 
Previously Held by Cessna Aircraft Company), Model 680 airplanes, 
certificated in any category, as identified in paragraphs (c)(1) and 
(c)(2) of this AD.
    (1) Model 680 Sovereign airplanes (commonly known as Citation 
Sovereign airplanes), having serial numbers: 680-0001, -0002, -0006, 
-0025, -0030, -0031, -0032, -0046, -0051, -0057, -0064, -0066, -
0067, -0082, -0104, -0108, -0112, -0118, -0120, -0125, -0132, -0139, 
-0140, -0141, -0144, -0147, -0148, -0149, -0153, -0157, -0160, -
0162, -0163, -0164, -0166, -0167, -0169, -0170, -0171, -0173, -0174, 
-0175, -0176, -0177, -0178, -0179, -0180, -0182, -0183, -0185, -
0186, -0192, -0193, -0196, -0200, -0202, -0204, -0205, -0206, -0208, 
-0211, -0216, -0220, -0221, -0222, -0227, -0229, -0230, -0231, -
0234, -0235, -0236, -0238, -0241, -0242, -0243, -0245, -0246, -0249, 
-0252, -0253, -0255, -0256, -0257, -0258, -0260, -0262, -0268, -
0270, -0271, -0280, -0282, -0283, -0284, -0285, -0289, -0291, -0292, 
-0296, -0297, -0300, -0301, -0302, -0303, -0304, -0306, -0307, -
0313, -0315, -0317, -0318, -0322, -0323, -0324, -0327, -0328, -0329, 
-0333, -0334, -0336, -0337, -0339, -0340, -0342, -0344, -0346, -
0347, -0348, and -0349.
    (2) Model 680 Sovereign airplanes (commonly known as Citation 
Sovereign+ airplanes) having serial numbers: 680-0501, -0504, -0505, 
-0509, -0510, -0511, -0512, -0513, -0514, -0515, -0516, -0517, -
0519, -0520, -0522, -0524, -0525, -0526, -0527, and -0531.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by Cessna's report of a manufacturing 
defect which affects the durability of the aft canted bulkhead 
metallic structure. The manufacturing defect directly affects the 
bond integrity of the vertical and horizontal stiffeners on the aft 
canted bulkhead metallic structure. We are issuing this AD to 
prevent disbonding of the horizontal and vertical stiffeners on the 
aft canted bulkhead. Loss of bond integrity could result in a 
structural failure that may lead to separation of the cruciform tail 
and loss of control of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Before the accumulation of 7,000 total flight hours, or within 
100 flight hours after the effective date of this AD, whichever 
occurs later, perform a general visual inspection for disbonding and 
paint cracking around the edges of the stiffeners on the aft canted 
bulkhead, in accordance with the Accomplishment Instructions of 
Cessna Service Letter SL680-53-05, Revision 2, dated September 30, 
2015. Repeat the general visual inspection thereafter at intervals 
not to exceed 100 flight hours, until the modification required by 
paragraph (i) of this AD is accomplished.

(h) Repair

    If, during any inspection required by paragraph (g) of this AD, 
any disbonding or cracked paint is found, before further flight, 
repair in accordance with a method approved by the Manager, Wichita 
Aircraft Certification Office (ACO), ACE-118W, FAA.

(i) Modification

    At the applicable compliance time specified in paragraph (i)(1) 
or (i)(2) of this

[[Page 9793]]

AD, modify the airplane by installing additional stiffeners on the 
aft canted bulkhead, in accordance with the Accomplishment 
Instructions of Cessna Service Bulletin SB680-53-08, dated September 
28, 2015. Doing this modification terminates the repetitive 
inspections required by paragraph (g) of this AD.
    (1) For airplanes that have accumulated 7,000 or more total 
flight hours as of the effective date of this AD: Within 1,800 
flight hours or 24 months, whichever occurs first, after the 
effective date of this AD.
    (2) For airplanes that have accumulated less than 7,000 total 
flight hours as of the effective date of this AD: Within 3,600 
flight hours or 48 months, whichever occurs first, after the 
effective date of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using the service information identified in 
paragraph (j)(1) or (j)(2) of this AD, which is not incorporated by 
reference in this AD.
    (1) Cessna Service Letter SL680-53-05, dated December 22, 2014.
    (2) Cessna Service Letter SL680-53-05, Revision 1, dated March 
12, 2015.

(k) No Reporting Requirement

    Although Cessna Service Bulletin SB680-53-08, dated September 
28, 2015; and Cessna Service Letter SL680-53-05 Revision 2, dated 
September 30, 2015; specify to submit certain information to the 
manufacturer, this AD does not include that requirement.

(l) Special Flight Permit

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita ACO, ACE-118W, 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 (n)(1) 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.

(n) Related Information

    (1) For more information about this AD, contact Paul Kalowski, 
Aerospace Engineer, Airframe Branch, ACE-118W, FAA, Wichita ACO, 
1801 Airport Road, Room 100, Dwight D. Eisenhower Airport, Wichita, 
KS 67209; phone: 316-946-4186; fax: 316-946-4107; email: 
paul.kalowski@faa.gov.
    (2) For service information identified in this AD, contact 
Textron Aviation Inc., P.O. Box 7706, Wichita, KS 67277; telephone: 
316-517-6215; fax: 316-517-5802; email: citationpubs@txtav.com; 
Internet: https://support.cessna.com/custsupt/csupport/newlogin.jsp. 
You may view this 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 February 18, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04136 Filed 2-25-16; 8:45 am]
BILLING CODE 4910-13-P