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[Federal Register Volume 79, Number 65 (Friday, April 4, 2014)]
[Proposed Rules]
[Pages 18848-18850]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-07520]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0187; Directorate Identifier 2012-NM-087-AD]
RIN 2120-AA64

Airworthiness Directives; Hawker Beechcraft Corporation 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 
certain Hawker Beechcraft Corporation (Type Certificate previously held 
by Mitsubishi; Raytheon Aircraft Company) Model MU-300 airplanes, and 
Hawker Beechcraft Corporation (Type Certificate previously held by 
Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400, 400A, 
and 400T airplanes. This proposed AD was prompted by multiple reports 
of fatigue cracking in the horizontal stabilizer ribs. This proposed AD 
would require repetitive inspections of the horizontal stabilizer rib 
assemblies for cracking, and replacement if necessary. We are proposing 
this AD to detect and correct such cracking, which could result in the 
failure of the horizontal stabilizer and loss of pitch control of the 
airplane.

DATES: We must receive comments on this proposed AD by May 19, 2014.

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-2014-
0187; 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 Chapman, Aerospace Engineer, 
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office 
(ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, 
Kansas 67209; telephone (316) 946-4152; fax (316) 946-4107.

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-2014-0187; 
Directorate Identifier 2012-NM-087-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 propose to adopt a new airworthiness directive (AD) for certain 
Hawker Beechcraft Corporation (Type Certificate previously held by 
Mitsubishi; Raytheon Aircraft Company) Model MU-300 airplanes, and 
Hawker Beechcraft Corporation (Type Certificate previously held by 
Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400, 400A, 
and 400T airplanes. We have received multiple reports of fatigue 
cracking in the horizontal stabilizer ribs. This condition, if not 
corrected, could result in failure of the horizontal stabilizer and 
loss of pitch control of the airplane.

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.

[[Page 18849]]

Proposed AD Requirements

    This proposed AD would require repetitive radiographic (x-ray) 
inspections or borescope inspections for cracking of the horizontal 
stabilizer rib assemblies, and replacement if necessary, in accordance 
with a method approved by the Manager, Wichita Aircraft Certification 
Office (ACO), FAA.

Costs of Compliance

    We estimate that this proposed AD affects 735 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                Action                            Labor cost            Parts cost      Cost per product                Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection............................  20 work-hours x $85 per hour =        $30   $1,730 per inspection     $1,271,550 per inspection cycle.
                                         $1,700 per inspection cycle.                cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement...............................  280 work-hours x $85 per hour =             $8,321          $32,121
                                             $23,800.
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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, 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):

Hawker Beechcraft Corporation (Type Certificate Previously held by 
Raytheon Aircraft Company; Beech Aircraft Corporation); and Hawker 
Beechcraft Corporation (Type Certificate Previously held by 
Mitsubishi; Raytheon Aircraft Company): Docket No. FAA-2014-0187; 
Directorate Identifier 2012-NM-087-AD.

(a) Comments Due Date

    We must receive comments by May 19, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) through (c)(5) of this AD.
    (1) Hawker Beechcraft Corporation (Type Certificate previously 
held by Mitsubishi; Raytheon Aircraft Company) Model MU-300 
airplanes, serial numbers A003SA through A093SA inclusive.
    (2) Hawker Beechcraft Corporation (Type Certificate previously 
held by Raytheon Aircraft Company; Beech Aircraft Corporation) Model 
400 airplanes, serial numbers RJ-1 through RJ-65 inclusive.
    (3) Hawker Beechcraft Corporation (Type Certificate previously 
held by Raytheon Aircraft Company; Beech Aircraft Corporation) Model 
400A airplanes, serial numbers RK-1 through RK-604 inclusive.
    (4) Hawker Beechcraft Corporation (Type Certificate previously 
held by Raytheon Aircraft Company; Beech Aircraft Corporation) Model 
400T (T-1A) airplanes, serial numbers TT-1 through TT-180 inclusive.
    (5) Hawker Beechcraft Corporation (Type Certificate previously 
held by Raytheon Aircraft Company; Beech Aircraft Corporation) Model 
400T (TX), serial numbers TX-1 through TX-13 inclusive.

 (d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by multiple reports of fatigue cracking in 
the horizontal stabilizer ribs. We are issuing this AD to detect and 
correct such cracking, which could result in the failure of the 
horizontal stabilizer and loss of pitch control of the airplane.

[[Page 18850]]

(f) Compliance

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

 (g) Repetitive Inspections

    Before the accumulation of 7,400 total flight hours or within 6 
months after the effective date of this AD, whichever occurs later, 
perform a radiographic (x-ray) inspection or a borescope inspection 
for cracking of the horizontal stabilizer rib assemblies, in 
accordance with a method approved by the Manager, Wichita Aircraft 
Certification Office (ACO), FAA. Repeat the inspection thereafter at 
intervals not to exceed 2,400 flight hours. For an inspection method 
to be approved by the Manager, Wichita ACO, as required by this 
paragraph, the Manager's approval letter must specifically refer to 
this AD.

(h) Replacement

    If any cracking is found during any inspection required by 
paragraph (g) of this AD: Before further flight, replace the 
horizontal rib assemblies with new horizontal rib assemblies, in 
accordance with method to be approved by the Manager, Wichita ACO. 
For a replacement method to be approved by the Manager, Wichita ACO, 
as required by this paragraph, the Manager's approval letter must 
specifically refer to this AD. This replacement does not terminate 
the repetitive inspection requirements of paragraph (g) of this AD.

(i) Special Flight Permit

    Special flight permits may be issued in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the airplane to a location where the airplane 
can be repaired (if the operator elects to do so), provided the 
restrictions specified in paragraphs (i)(1) through (i)(4) of this 
AD are followed.
    (1) Do not exceed 10 flight hours of operation.
    (2) Only operations under daylight conditions and under visual 
flight rules are allowed.
    (3) Only operations with the minimum flightcrew and with no 
passengers are allowed.
    (4) Do not exceed maneuver speed as specified in the applicable 
airplane flight manual.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Airframe Branch, 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 the Related Information section 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.

(k) Related Information

    For more information about this AD, contact Paul Chapman, 
Aerospace Engineer, Airframe Branch, ACE-118W, FAA, Wichita Aircraft 
Certification Office (ACO), 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4152; 
fax (316) 946-4107.

    Issued in Renton, Washington, on March 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-07520 Filed 4-3-14; 8:45 am]
BILLING CODE 4910-13-P
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