Airworthiness Directives; Cessna Aircraft Company Airplanes

[Federal Register Volume 80, Number 68 (Thursday, April 9, 2015)]
[Rules and Regulations]
[Pages 19017-19019]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-07705]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0839; Directorate Identifier 2015-CE-006-AD; 
Amendment 39-18131; AD 2015-07-03]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Cessna Aircraft Company (Cessna) Model 402C and 414A airplanes. This AD 
requires repetitively inspecting the engine mount beams for cracks and 
contacting Cessna for FAA-approved corrective action if cracks are 
found. This AD also requires sending an inspection report to the FAA 
and to Cessna. This AD was prompted by reports of cracks found across 
the engine mount beams. We are issuing this AD to correct the unsafe 
condition on these products.

DATES: This AD is effective April 24, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 24, 
2015.
    We must receive comments on this AD by May 26, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Cessna 
Aircraft Company, Customer service, P.O. Box 7706, Wichita, KS 67277; 
telephone: (316) 517-5800; fax: (316) 517-7271; email: 
[email protected]; Internet: http://www.cessnasupport.com. You may review this 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. It is also available on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2015-0839.

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-2015-
0839; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita 
Aircraft Certification Office, FAA, 1801 S. Airport Road, Room 100, 
Wichita, Kansas 67209; phone: (316) 946-4123; fax: (316) 946-4107; 
email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We received reports of cracks found on the engine mount beams of 
certain Cessna Aircraft Company (Cessna) Model 402C airplanes. The 
cracks found run across the beam and extend beyond the doubler located 
under the aft engine mount and aft of the forward engine mount. 
Investigation revealed that the cause of the cracks is fatigue.
    The engine beam mounts of the Cessna Model 402C airplanes are the 
same type design as that of the Cessna Model 414A airplanes.
    This condition, if not detected and corrected, could result in 
failure of an engine mount beam and could lead to engine separation 
with consequent loss of power and loss of control. We are issuing this 
AD to correct the unsafe condition on these products.

Relevant Service Information Under 1 CFR Part 51

    We reviewed Cessna Aircraft Company Multi-engine Service Letter No. 
MEL-54-01, dated March 20, 2015, including the undated Attachment, 
``Inspection Results Form.'' The Cessna Aircraft Company Multi-engine 
Service Letter describes procedures for inspecting the engine mount 
beams for cracks and reporting the inspection results to Cessna. This 
information is reasonably available at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-0839, or you may see 
ADDRESSES for other ways to access this service information.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires repetitively inspecting the engine mount beams for 
cracks and contacting Cessna for an FAA-approved corrective action if 
cracks are found. This AD also requires sending the inspection results 
to the FAA and to Cessna.

Differences Between This AD and the Service Information

    Cessna Aircraft Company Multi-engine Service Letter No. MEL-54-01, 
dated March 20, 2015, including the undated Attachment, ``Inspection 
Results Form,'' specifies reporting the inspection results to Cessna. 
In this AD, we also require that the inspection results be reported to 
the FAA.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this

[[Page 19018]]

AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
cracks in the engine mount beam could cause the engine mount beam to 
fail and lead to engine separation with consequent loss of power and 
loss of control. Therefore, we find that notice and opportunity for 
prior public comment are impracticable and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2015-0839 and 
Directorate Identifier 2015-CE-006-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to 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 AD.

Costs of Compliance

    We estimate that this AD affects 555 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                    Labor cost            Parts cost      Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Prepare airplane for             3 work-hours x $85 per  Not applicable...  $255 per           $141,525 per
 inspections.                     hour = $255 per                            inspection cycle.  inspection cycle
                                  inspection cycle.
X-ray inspection of the engine   8 work-hours x $85 per  $180.............  $860 per           $477,300 per
 mount beams (4 engine mount      hour = $680 per                            inspection cycle.  inspection cycle
 beams per airplane).             inspection cycle.
Eddy current inspection of the   1 work-hour x $85 per   Not applicable...  $85 per            $47,175 per
 engine mount beams (4 engine     hour = $85 per                             inspection cycle.  inspection cycle
 mount beams per airplane).       inspection cycle.
Visual inspection of the engine  1 work-hour x $85 per   Not applicable...  $85 per            $47,175 per
 mount beams (4 engine mount      hour = $85 per                             inspection cycle.  inspection cycle
 beams per airplane).             inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have no way of knowing the extent of cracks that may be found 
during the required inspections. Therefore, we have no way of 
determining the cost of the corrective action.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591. ATTN: Information 
Collection Clearance Officer, AES-200.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation Programs'' 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

[[Page 19019]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-07-03 Cessna Aircraft Company: Amendment 39-18131; Docket No. 
FAA-2015-0839; Directorate Identifier 2015-CE-006-AD.

(a) Effective Date

    This AD is effective April 24, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Cessna Aircraft Company Model 402C airplanes, 
serial numbers 402C0001 through 402C1020, and Model 414A airplanes, 
serial numbers 414A0001 through 414A1212, certificated in any 
category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 54, Nacelles/Pylons.

(e) Unsafe Condition

    This AD was prompted by reports of cracks found on the engine 
mount beams. We are issuing this AD to prevent failure of the engine 
mount beams, which could lead to engine separation with consequent 
loss of power and loss of control.

(f) Compliance

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

(g) Inspect Engine Mount Beams

    At the compliance times specified in paragraphs (g)(1) through 
(g)(4) of this AD, inspect each engine mount beam using radiographic 
(x-ray), eddy current, and visual methods following the 
Accomplishment Instructions in Cessna Aircraft Company Multi-engine 
Service Letter No. MEL-54-01, dated March 20, 2015. If total hours 
time-in-service (TIS) on an engine mount beam is unknown, use the 
airplane's total hours TIS.
    (1) For each engine mount beam that has accumulated less than 
20,000 hours TIS, initially inspect at whichever of the following 
that occurs later and repetitively thereafter at intervals not to 
exceed 200 hours TIS as long as no cracks are found:
    (i) At or before the accumulation of 15,000 hours TIS on each 
engine beam; or
    (ii) Within the next 100 hours TIS after the effective date of 
this AD or within the next 90 days after the effective date of this 
AD, whichever occurs first.
    (2) For each engine mount beam that has accumulated 20,000 hours 
TIS but no more than 24,999 hours TIS, initially inspect at 
whichever of the following that occurs first and repetitively 
thereafter at intervals not to exceed 200 hours TIS as long as no 
cracks are found:
    (i) Within the next 75 hours TIS after the effective date of 
this AD; or
    (ii) Within the next 60 days after the effective date of this 
AD.
    (3) For each engine mount beam that has accumulated 25,000 hours 
TIS but no more than 30,000 hours TIS, initially inspect at 
whichever of the following that occurs first and repetitively 
thereafter at intervals not to exceed 200 hours TIS as long as no 
cracks are found:
    (i) Within the next 50 hours TIS after the effective date of 
this AD; or
    (ii) Within the next 45 days after the effective date of this 
AD.
    (4) For each engine mount beam that has accumulated more than 
30,000 hours TIS, initially inspect at whichever of the following 
that occurs first and repetitively thereafter at intervals not to 
exceed 200 hours TIS as long as no cracks are found:
    (i) Within the next 25 hours TIS after the effective date of 
this AD; or
    (ii) Within the next 30 days after the effective date of this 
AD.

(h) Contact Cessna Aircraft Company

    If any cracks are found during any inspection required in 
paragraphs (g)(1) through (g)(4) of this AD, before further flight, 
contact Cessna Aircraft Company at the address specified in 
paragraph (m)(3) of this AD for an FAA-approved corrective action 
developed specifically for this AD.

(i) Reporting Requirement

    Within 10 days after each inspection required in paragraphs 
(g)(1) through (g)(4) of this AD or within 10 days after the 
effective date of this AD, whichever occurs later, using the undated 
Attachment, ``Inspection Results Form,'' to Cessna Aircraft Company 
Multi-engine Service Letter No. MEL-54-01, dated March 20, 2015, 
report the results to the FAA, Wichita Aircraft Certification Office 
(ACO) at the address specified in paragraph (l) of this AD. Report 
the result of each inspection to the FAA, Wichita ACO, for one year 
after the date of the initial inspection required in paragraphs 
(g)(1) through (g)(4) of this AD. Also report the results of the 
initial inspection to Cessna at the address specified in paragraph 
(m)(3) of this AD.

(j) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
ACO, send it to the attention of the person identified in 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.

(l) Related Information

    Gary Park, Aerospace Engineer, Wichita ACO, FAA, 1801 S. Airport 
Road, Room 100, Wichita, Kansas 67209; phone: (316) 946-4123; fax: 
(316) 946-4107; continued operational safety email: [email protected]; engineer contact email: [email protected].

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Cessna Aircraft Company Multi-engine Service Letter No. MEL-
54-01, dated March 20, 2015, including the undated Attachment, 
``Inspection Results Form.''
    (ii) Reserved.
    (3) For Cessna Aircraft Company service information identified 
in this AD, contact Cessna Aircraft Company, Customer service, P.O. 
Box 7706, Wichita, KS 67277; telephone: (316) 517-5800; fax: (316) 
517-7271; email: [email protected]; Internet: http://www.cessnasupport.com.
    (4) You may view this 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2015-0839.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Kansas City, Missouri, on March 30, 2015.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2015-07705 Filed 4-8-15; 8:45 am]
 BILLING CODE 4910-13-P

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