[Federal Register Volume 71, Number 174 (Friday, September 8, 2006)]
[Rules and Regulations]
[Pages 52983-52988]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-7511]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25760; Directorate Identifier 2006-CE-48-AD; 
Amendment 39-14757; AD 2006-18-51]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Models 1900, 
1900C, and 1900D Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Raytheon Aircraft Company (RAC) Models 1900, 1900C, and 1900D 
airplanes. This AD contains the same information as emergency AD 2006-
18-51 and publishes the action in the Federal Register. This AD 
requires you to do a one-time visual inspection of both the left and 
right wing rear spar lower caps for cracking and other damage such as 
loose or missing fasteners; repair any cracks or damage found; and 
report any cracks or damage found to the FAA and RAC. This AD results 
from extensive cracks found in the wing rear spar lower caps and rear 
spar web of two of the affected airplanes. One of the airplanes also 
had missing fasteners. We are issuing this AD to detect and correct 
cracking and other damage in the wing rear spar lower caps of the 
affected airplanes before the cracks or damage lead to failure. Such a 
wing failure could result in the wing separating from the airplane with 
consequent loss of control.

DATES: This AD becomes effective on September 8, 2006.
    We must receive any comments on this AD by November 7, 2006.

ADDRESSES: Use one of the following addresses to comment on this 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 20590-0001.
     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.
    To view the comments to this AD, go to http://dms.dot.gov. The 
docket number is FAA-2006-25760; Directorate Identifier 2006-CE-48-AD.

FOR FURTHER INFORMATION CONTACT: Steven E. Potter, FAA, 1801 Airport 
Road, Wichita, Kansas 67209; telephone: (316) 946-4124; fax: (316) 946-
4107.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA received recent reports of cracks found in the wings of two 
RAC 1900D airplanes. During routine maintenance, the wing rear spar 
lower caps and rear spar web were found to have significant cracks.
    The RAC Structural Inspection Manual requires a thorough inspection 
of the wing rear spar at 17,500 hours time-in-service (TIS) with 
repetitive inspections at intervals of 3,000 hours TIS.

[[Page 52984]]

    One airplane had 19,126 hours TIS when cracks were found. The 
cracks were in the lower aft spar cap flange, but the cracks extended 
upward into the web and terminated at the lightening hole in the spar 
web. Fasteners were also found missing in the spar cap and wing cove 
splice plate. There were no discrepancies recorded from the initial 
inspection at 17,500 hours TIS on this airplane.
    Early indications show similar cracking on the other airplane. We 
continue to gather information on this airplane.
    Analysis shows that similar cracks could also develop in the wings 
of the Models 1900 and 1900C airplanes.
    Cracking in the wing rear spar lower caps, if not corrected, could 
result in wing failure. Such a wing failure could result in the wing 
separating from the airplane with consequent loss of control.
    On August 31, 2006, FAA issued emergency AD 2006-18-51 to require 
you to do a one-time visual inspection of both the left and right wing 
rear spar lower caps for cracking and other damage such as loose or 
missing fasteners; repair any cracks or damage found; and report any 
cracks or damage found to the FAA and RAC.

FAA's Determination

    The FAA determined that immediate corrective action was required, 
that notice and opportunity for prior public comment were impracticable 
and contrary to the public interest, and that good cause existed to 
make the AD effective immediately by individual letters issued on 
August 31, 2006, to all known U.S. operators of the affected RAC Models 
1900, 1900C, and 1900D airplanes. These conditions still exist, and the 
AD is published in the Federal Register as an amendment to section 
39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it 
effective to all persons.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and an opportunity for 
public comment. We invite you to send any written relevant data, views, 
or arguments regarding this AD. Send your comments to an address listed 
under the ADDRESSES section. Include the docket number ``FAA-2006-
25760; Directorate Identifier 2006-CE-48-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the 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 AD.

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 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); 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 AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the 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) 647-5227) 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.

Adoption of the Amendment

0
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):

2006-18-51 Raytheon Aircraft Company (RAC): Amendment 39-14757; 
Docket No. FAA-2005-25760; Directorate Identifier 2006-CE-48-AD.

Effective Date

    (a) This AD becomes effective on September 8, 2006.

Affected ADs

    (b) None.

Applicability

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

------------------------------------------------------------------------
                  Models                            Serial Nos.
------------------------------------------------------------------------
(1) 1900.................................  UA-3.
(2) 1900C (C-12J)........................  UB-1 through UB-74, UC-1
                                            through UC-174, and UD-1
                                            through UD-6.
(3) 1900D................................  UE-1 through UE-439.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD is the result of extensive cracks found in the wing 
rear spar lower caps and rear spar web of two of the affected 
airplanes. One of the airplanes also had missing fasteners. We are 
issuing this AD to detect and correct cracking and other damage in 
the wing rear spar lower caps of the affected airplanes before the 
cracks or damage lead to failure. Such a wing failure could result 
in the wing separating from the airplane with consequent loss of 
control.

Compliance

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

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               Actions                             Compliance                            Procedures
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(1) A one-time visual inspection of   At whichever occurs later after       Follow the procedures in the
 both the left and right wing rear     September 8, 2006 (the effective      Appendix to this AD.
 spar lower caps for cracks and        date of this AD), except to those
 other damage such as loose or         who received emergency AD 2006-18-
 missing fasteners.                    51, which contained the
                                       requirements of this amendment and
                                       became effective immediately upon
                                       receipt:
                                      (i) Within 24 hours; or
                                      (ii) Prior to further flight.
(2) For the inspection in paragraph   For this repositioning, you may       The following limitations are
 (e)(1) of this AD, you may return/    operate the airplane up to 3 hours    imposed for such a repositioning
 position the airplane to a home       time-in-service provided the          flight:
 base, hangar, maintenance facility,   flight(s) occur(s) no later than 30  (i) ONLY THE PILOT AND ANY
 etc.                                  days after September 8, 2006 (the     ADDITIONAL FLIGHT CREW MEMBER
                                       effective date of this AD), except    REQUIRED FOR SAFE OPERATION IS
                                       to those who received emergency AD    ALLOWED FOR THIS FLIGHT;
                                       2006-18-51, which contained the      (ii) FLIGHT INTO KNOWN OR FORECAST
                                       requirements of this amendment and    MODERATE OR SEVERE TURBULENCE IS
                                       became effective immediately upon     PROHIBITED; and
                                       receipt.                             (iii) INDICATED AIRSPEED IS LIMITED
                                                                             TO 175 KNOTS MAXIMUM.
(3) Repair any cracks or other        Before further flight after the       Contact RAC at Post Office Box 85,
 damage such as loose or missing       inspection required by paragraph      Wichita, Kansas 67201-0085; phone:
 fasteners found during the            (e)(1) of this AD.                    316-676-8366; fax: (316) 676-8745;
 inspection required in paragraph                                            e-mail: tom--
 (e)(1) of this AD. Do this by                                               [email protected].
 obtaining and incorporating an FAA-
 approved repair scheme from RAC.
(4) Report the inspection results to  Within 72 hours after completing the  Send your report to Steven E.
 the FAA and RAC. For the reporting    inspection required in paragraph      Potter, FAA, 1801 Airport Road,
 requirement in this AD, under the     (e)(1) of this AD.                    Wichita, Kansas 67209; fax: (316)
 provisions of the Paperwork                                                 946-4107; e-mail:
 Reduction Act, the Office of                                                [email protected]; and Tom
 Management and Budget (OMB) has                                             Peay, Raytheon Aircraft Company,
 approved the information collection                                         Post Office Box 85, Wichita, Kansas
 requirements and has assigned OMB                                           67201-0085; fax: (316) 676-8745; e-
 Control Number 2120-0056.                                                   mail: [email protected].
                                                                             Include in your report the
                                                                             following information:
                                                                            (i) Aircraft model and serial
                                                                             number;
                                                                            (ii) Number of cycles;
                                                                            (iii) Aircraft hours TIS;
                                                                            (iv) Left and right wing lower spar
                                                                             cap hours TIS;
                                                                            (v) Hours TIS on the spar cap since
                                                                             last inspection;
                                                                            (vi) Answer yes or no whether
                                                                             cracking, missing fasteners, or
                                                                             other damage was found; and
                                                                            (vii) If cracking was found,
                                                                             identify size and location of
                                                                             cracks.
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Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Wichita Aircraft Certification Office, FAA, 
ATTN: Steven E. Potter, FAA, 1801 Airport Road, Wichita, Kansas 
67209; telephone: (316) 946-4124; fax: (316) 946-4107, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures in 14 CFR 39.

APPENDIX TO AD 2006-18-51

Inspection Instructions--Raytheon Aircraft Company 1900 Series Wing 
Rear Spar

    Step 1. Lower the wing flaps to provide visual access to the 
wing rear spar cove area. Although the pictures show the flaps 
removed, this AD does not require flap removal to do the inspection.
    Step 2. Using a strong, high-intensity light visually inspect 
the area of the wing rear spar identified in Figure 1. There is 
ample visually visual access from above the upper surface of the 
flap. Look for cracks (like those shown in Figures 2 and 3) and 
loose or missing fasteners.
    Step 3. Clean the wing rear spar area 10 inches inboard and 
outboard of the buttock line (BL) 114 area.
    Step 4. Repeat the Step 2 inspection.
BILLING CODE 4910-13-U

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[GRAPHIC] [TIFF OMITTED] TR08SE06.002


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[GRAPHIC] [TIFF OMITTED] TR08SE06.003


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[GRAPHIC] [TIFF OMITTED] TR08SE06.004


    Issued in Kansas City, Missouri, on September 1, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-7511 Filed 9-7-06; 8:45 am]
BILLING CODE 4910-13-C