Document ID: FAA-2007-29240-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Cessna Aircraft Company Models 175 and 175A Airplanes
Posted Date: 2008-04-08T04:00Z

[Federal Register: April 8, 2008 (Volume 73, Number 68)]
[Proposed Rules]               
[Page 19017-19019]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08ap08-17]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29240; Directorate Identifier 2007-CE-076-AD]
RIN 2120-AA64

 
Airworthiness Directives; Cessna Aircraft Company Models 175 and 
175A Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Cessna Aircraft Company (Cessna) Models 175 and 175A airplanes. 
This proposed AD would require 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 
proposed AD would require 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 
would be required by this proposed AD. This proposed AD was prompted by 
a report that the engine became detached from the firewall during 
landing on one of the affected airplanes. We are proposing 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.

DATES: We must receive comments on this proposed AD by June 9, 2008.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     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.
     Fax: (202) 493-2251.
     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.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
    For service information identified in this proposed AD, contact 
Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, 
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2007-29240; Directorate Identifier 2007-CE-076-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact we 
receive concerning this proposed AD.

Discussion

    We received a report of the engine detaching from the firewall on a 
Cessna Model 175 airplane during landing. Investigation revealed that 
cracks in the two top engine mounting brackets behind the firewall 
caused the brackets to fail. This resulted in the top half of the 
firewall failing, pulling forward and down about 18 inches.
    The National Transportation Safety Board (NTSB) Materials 
Laboratory examined the cracked brackets. The examination revealed that 
the metal content of the brackets did not contain the constituent 
elements of the specified material and was approximately 40 percent 
below the specified strength. The NTSB determined that reduced 
structural integrity of the engine mounting brackets resulted in 
fatigue cracks developing in the brackets.
    We agree with the NTSB's determination that inadequate materials 
used in manufacturing the engine mounting brackets, which were used on

[[Page 19018]]

Cessna Models 175 and 175A airplanes manufactured from 1958 through 
1960, caused the engine mounting brackets to crack.
    This condition, if not corrected, could cause the engine mounting 
brackets to fail. This failure could result in the engine detaching 
from the firewall.

Relevant Service Information

    We have 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.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This proposed AD 
would require 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 proposed AD would 
require 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 would be required 
by this proposed AD. This proposed AD would require you to use the 
service information described previously to perform these actions.

Costs of Compliance

    We estimate that this proposed 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 the 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.
------------------------------------------------------------------------

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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the proposed AD, the 
regulatory evaluation, any comments received, and other information on 
the Internet at http://dms.dot.gov; or in person at the Docket 
Management Facility between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Office (telephone (800) 647-5527) 
is located at the street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Cessna Aircraft Company: Docket No. FAA-2007-29240; Directorate 
Identifier 2007-CE-076-AD.

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by June 9, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following airplane models and serial 
numbers that are certificated in any category:

[[Page 19019]]

----------------------------------------------------------------------------------------------------------------
                  Model                              Serial Nos.                      Year manufactured
----------------------------------------------------------------------------------------------------------------
(1) 175.................................  55001 through 55703.............  1958.
(2) 175.................................  55704 through 56238.............  1959.
(3) 175.................................  28700A, 626, and 640............  1958 and 1959.
(4) 175A................................  691, and 56239 through 56777....  1960.
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

    (d) A report that the engine became unattached from the firewall 
during landing on one of the affected airplanes prompts this AD. 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.

Compliance

    (e) To address this problem, you must do the following, unless 
already done:

----------------------------------------------------------------------------------------------------------------
                 Actions                            Compliance                         Procedures
----------------------------------------------------------------------------------------------------------------
(1) Check the airplane logbook to          Within the next 30 days      The owner/operator holding at least a
 determine if all four of the original      after the effective date     private pilot certificate as authorized
 engine mounting brackets have been         of this AD.                  by section 43.7 of the Federal Aviation
 replaced.                                                               Regulations (14 CFR 43.7) may do this
                                                                         action.
(2) If you can positively determine that   Not applicable.............  Make an entry into the aircraft logbook
 all four of the original engine mounting                                showing compliance with this portion of
 brackets have been replaced, no further                                 the AD in accordance with section 43.9
 action is required.                                                     of the Federal Aviation Regulations (14
                                                                         CFR 43.9). The owner/operator holding
                                                                         at least a private pilot certificate as
                                                                         authorized by section 43.7 of the
                                                                         Federal Aviation Regulations (14 CFR
                                                                         43.7) may do this action.
(3) If you cannot positively determine     Initially inspect within     Follow Cessna Single Engine Service
 that all four of the original engine       the next 12 months after     Bulletin SEB07-2, Revision 2, dated
 mounting brackets have been replaced,      the effective date of this   June 18, 2007.
 inspect each of the upper and lower        AD. If no cracks are
 engine mounting brackets on both the       found, repetitively
 left and right sides for cracks as         inspect thereafter at
 specified in the service bulletin.         intervals not to exceed
                                            500 hours time-in-service
                                            (TIS) until all four of
                                            the original engine
                                            mounting brackets are
                                            replaced.
(4) If cracks are found in any of the      Before further flight after  Follow Cessna Single Engine Service
 engine mounting brackets during any        the inspection in which      Bulletin SEB07-2, Revision 2, dated
 inspection required in paragraph (e)(3)    cracks are found.            June 18, 2007.
 of this AD, replace the cracked engine     Replacing the cracked
 mounting bracket(s).                       engine mounting bracket
                                            terminates the repetitive
                                            inspection required in
                                            paragraph (e)(3) of this
                                            AD only for the replaced
                                            engine mounting bracket.
(5) To terminate the repetitive            At any time before or after  Follow Cessna Single Engine Service
 inspections required in paragraph (e)(3)   the initial inspection       Bulletin SEB07-2, Revision 2, dated
 of this AD, you may replace all four       required in paragraph        June 18, 2007.
 original engine mounting brackets.         (e)(3) of this AD.
(6) Dispose of every replaced bracket      Before further flight after  Not applicable.
 following 14 CFR 43.10, paragraph          the engine mounting
 (c)(6), which states the following:        bracket is removed for
 ``Mutilation. The part may be mutilated    replacement.
 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.''
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) 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. Send information to 
ATTN: Gary Park, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport 
Road, Room 100, Wichita, Kansas 67209; telephone: 316-946-4123; fax: 
316-946-4107; e-mail address: gary.park@faa.gov. Before using any 
approved AMOC on any airplane to which the AMOC applies, notify your 
appropriate principal inspector (PI) in the FAA Flight Standards 
District Office (FSDO), or lacking a PI, your local FSDO.

Related Information

    (g) To get copies of the service information referenced in this 
AD, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, 
Wichita, Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-
9006. To view the AD docket, go to U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or 
on the Internet at http://dms.dot.gov. The docket number is Docket 
No. FAA-2007-29240; Directorate Identifier 2007-CE-076-AD.

    Issued in Kansas City, Missouri, on March 31, 2008.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
 [FR Doc. E8-7258 Filed 4-7-08; 8:45 am]

BILLING CODE 4910-13-P