[Federal Register Volume 72, Number 102 (Tuesday, May 29, 2007)]
[Proposed Rules]
[Pages 29446-29447]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-10216]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 72, No. 102 / Tuesday, May 29, 2007 / 
Proposed Rules  

[[Page 29446]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28308; Directorate Identifier 2007-NM-016-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon (Beech) Model 400, 400A, and 
400T Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Raytheon (Beech) Model 400, 400A, and 400T series 
airplanes. This proposed AD would require modifying the attachment 
fasteners on the engine cowling panels. This proposed AD results from 
several reports of loose attachment fasteners found on the engine 
cowling panels, and subsequently the panels either peeling back or 
separating from the airplane during flight. We are proposing this AD to 
prevent failure of the attachment fasteners on the engine cowling 
panels, which could result in separation of a panel from the airplane, 
and consequent damage to airplane structure. These conditions could 
adversely affect continued safe flight and landing of the airplane, or 
cause injury to people or damage to property on the ground.

DATES: We must receive comments on this proposed AD by July 13, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Raytheon Aircraft Company, Department 62, P.O. Box 85, 
Wichita, Kansas, 67201-0085, for the service information identified in 
this proposed AD.

FOR FURTHER INFORMATION CONTACT: William Griffith, Aerospace Engineer, 
Airframe and Services Branch, ACE-118W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4116; fax (316) 
946-4107.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
28308; Directorate Identifier 2007-NM-016-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 with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    We have received several reports indicating loose attachment 
fasteners (\1/4\-turn fasteners not fully engaged) were found on the 
engine cowling panels on certain Raytheon (Beech) Model 400, 400A, and 
400T series airplanes. Subsequently, the cowling panels either peeled 
back or separated from the airplane during flight. In one incident a 
cowling piece departed the airplane and landed within 50 feet of a 
residence. Investigation revealed that the loose fasteners are not 
detected during the pre-flight inspection and that aerodynamic loads 
may forcibly separate the panel from the airplane during flight. The 
separation forces could result in the panel causing damage to the 
engine or nacelle installation, in addition to other parts of the 
airplane. These conditions could adversely affect continued safe flight 
and landing of the airplane, or cause injury to people or damage to 
property on the ground.

Relevant Service Information

    We have reviewed Raytheon Service Bulletin SB 54-3788, dated 
December, 2006. The service bulletin describes procedures for modifying 
the attachment fasteners on the engine cowling panels. Accomplishing 
the actions specified in the service information is intended to 
adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in

[[Page 29447]]

the service information described previously.

Costs of Compliance

    There are about 757 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 575 airplanes of 
U.S. registry. The proposed actions would take about 10 work hours per 
airplane, at an average labor rate of $80 per work hour. Required parts 
would cost about $400 per airplane. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $690,000, or 
$1,200 per airplane.

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. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Raytheon Aircraft Company (Formerly Beech): Docket No. FAA-2007-
28308; Directorate Identifier 2007-NM-016-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 13, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Raytheon (Beech) Model 400, 400A, and 
400T series airplanes, certificated in any category; as identified 
in Raytheon Service Bulletin SB 54-3788, dated December, 2006.

Unsafe Condition

    (d) This AD results from several reports of loose attachment 
fasteners found on the engine cowling panels, and subsequently the 
panels either peeling back or separating from the airplane during 
flight. We are issuing this AD to prevent failure of the attachment 
fasteners on the engine cowling panels, which could result in 
separation of a panel from the airplane, and consequent damage to 
airplane structure. These conditions could adversely affect 
continued safe flight and landing of the airplane, or cause injury 
to people or damage to property on the ground.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Modification

    (f) Within 200 flight hours after the effective date of this AD: 
Modify the attachment fasteners on the engine cowling panels by 
doing all the actions in accordance with the Accomplishment 
Instructions of Raytheon Service Bulletin SB 54-3788, dated 
December, 2006.

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
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.

    Issued in Renton, Washington, on May 22, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-10216 Filed 5-25-07; 8:45 am]
BILLING CODE 4910-13-P