Airworthiness Directives; Beechcraft Corporation Airplanes, 52870-52872 [2013-20853]

Download as PDF 52870 Proposed Rules Federal Register Vol. 78, No. 166 Tuesday, August 27, 2013 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. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0753; Directorate Identifier 2013–CE–025–AD] RIN 2120–AA64 Airworthiness Directives; Beechcraft Corporation Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Beechcraft Corporation (type certificate previously held by Hawker Beechcraft Corporation) Models 1900, 1900C, and 1900D airplanes. This proposed AD was prompted by reports of cracking in the front spar cap angles and hat section structure of the vertical stabilizer. This proposed AD would require inspections of the vertical stabilizer spar angles and hat section for cracks with corrective actions as necessary. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by October 11, 2013. 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. pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 SUMMARY: VerDate Mar<15>2010 13:35 Aug 26, 2013 Jkt 229001 • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Beechcraft Corporation at address: 10511 E. Central, Wichita, Kansas 67206; phone: (800) 429–5372 or (316) 676–3140; Internet: http://www.beechcraft.com/ customer_support/contact_us/. You may review copies of the 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; 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, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4152; fax: (316) 946–4107; email: paul.chapman@faa.gov. 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– 2013–0753; Directorate Identifier 2013– CE–025–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 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 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 were notified by Beechcraft Corporation of cracks found in the vertical stabilizer structure of Models 1900, 1900C, and 1900D airplanes. Out of 140 airplanes inspected, 56 cracks have been found. This condition, if not corrected, could lead to structural failure of the vertical stabilizer and result in loss of control. Relevant Service Information We reviewed Hawker Beechcraft Mandatory Service Bulletin SB 55–4114, dated August 2012; Hawker Beechcraft Corporation Model 1900/1900C Airliner Structural Inspection Manual, Part Number 98–30937G2, dated May 1, 2013; and Beechcraft Corporation Model 1900D Airliner Structural Inspection Manual, Part Number 129–590000– 65E5, dated May 1, 2013. The service information describes procedures for visually inspecting the vertical stabilizer spar angles and hat section. 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. Proposed AD Requirements This proposed AD would require doing visual inspections of the vertical stabilizer spar angles and hat section for cracks and taking corrective actions as necessary. Costs of Compliance We estimate that this proposed AD affects 400 airplanes. We estimate the following costs to comply with this proposed AD: E:\FR\FM\27AUP1.SGM 27AUP1 Federal Register / Vol. 78, No. 166 / Tuesday, August 27, 2013 / Proposed Rules 52871 ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Visual inspection of the vertical stabilizer spar angles and hat section. 1.5 work-hours × $85 per hour = $127.50. Not applicable ................................ $127.50 $51,000 We estimate the following costs to do any necessary repairs 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 repairs: ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Repair of the spar cap (right hand or left hand) .......... 30 work-hours × $85 per hour = $2,550 ...................... $600 $3,150 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. pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 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, VerDate Mar<15>2010 13:35 Aug 26, 2013 Jkt 229001 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation): Docket No. FAA–2013– 0753; Directorate Identifier 2013–CE– 025–AD. (a) Comments Due Date We must receive comments by October 11, 2013. (b) Affected ADs None. (c) Applicability This AD applies to the following Beechcraft Corporation airplanes, certificated in any category: Model Serial No. 1900 ................ 1900C ............. UA–3. UB–1 through UB–74, UC–1 through UC–174–6. UD–1 through UD–6. UE–1 through UE–439. 1900C (C–12J) 1900D ............. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by reports of cracking in the front spar cap angles and hat section of the vertical stabilizer structure. We are issuing this AD to detect and correct cracking in the vertical stabilizer structure, which could lead to structural failure of the vertical stabilizer and result in loss of control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Visual Inspections (1) For all airplanes: Within the next 600 hours time-in-service (TIS) after the effective date of this AD, inspect part number (P/N) 101–640011–3/–4 spar angles and P/N 114– 640000–25/–26 hat section for cracks following the Accomplishment Instructions in paragraph 3.A. of Hawker Beechcraft Mandatory Service Bulletin SB 55–4114, dated August 2012. (2) For Models 1900 and 1900C airplanes: Within 1,200 hours TIS after the initial inspection required in paragraph (g)(1) of this AD or within 2 years after the initial inspection required in paragraph (g)(1) of this AD, whichever occurs first, and repetitively thereafter at intervals not to exceed 1,200 hours TIS or 2 years, whichever occurs first, inspect P/N 101–640011–3 and P/N 101– 640011–4 spar cap angles for cracks. Follow Procedure 8 under Vertical Stabilizer in the ‘‘I’’ Check Procedures of Hawker Beechcraft Corporation Model 1900/1900C Airliner Structural Inspection Manual, Part Number 98–30937G2, dated May 1, 2013. (3) For Models 1900 and 1900C airplanes: Within 1,200 hours TIS after the initial inspection required in paragraph (g)(1) of this AD or within 2 years after the initial inspection required in paragraph (g)(1) of this AD, whichever occurs first, and repetitively thereafter at intervals not to exceed 1,200 hours TIS or 2 years, whichever occurs first, inspect P/N 114–640000–25 and P/N 114– E:\FR\FM\27AUP1.SGM 27AUP1 52872 Federal Register / Vol. 78, No. 166 / Tuesday, August 27, 2013 / Proposed Rules 640000–26 hat section for cracks. Follow Procedure 9 under Vertical Stabilizer in the ‘‘I’’ Check Procedures of Hawker Beechcraft Corporation Model 1900/1900C Airliner Structural Inspection Manual, Part Number 98–30937G2, dated May 1, 2013. (4) For Model 1900D airplanes: Within 1,200 hours TIS after the initial inspection required in paragraph (g)(1) of this AD or within 2 years after the initial inspection required in paragraph (g)(1) of this AD, whichever occurs first, and repetitively thereafter at intervals not to exceed 1,200 hours TIS or 2 years, whichever occurs first, inspect P/N 101–640011–3 and P/N 101– 640011–4 spar cap angles for cracks. Follow Procedure 6.b. under Vertical Stabilizer Canted Stabilizer Station (CSS 69.184 through VSS 91.10) in the ‘‘I’’ Check Procedures of Beechcraft Corporation Model 1900D Airliner Structural Inspection Manual, Part Number 129–590000–65E5, dated May 1, 2013. (5) For Model 1900D airplanes: Within 1,200 hours TIS after the initial inspection required in paragraph (g)(1) of this AD or within 2 years after the initial inspection required in paragraph (g)(1) of this AD, whichever occurs first, and repetitively thereafter at intervals not to exceed 1,200 hours TIS or 2 years, whichever occurs first, inspect P/N 114–640000–25 and P/N 114– 640000–26 hat section for cracks. Follow Procedure 6.c. under Vertical Stabilizer Canted Stabilizer Station (CSS 69.184 through VSS 91.10) in the ‘‘I’’ Check Procedures of Beechcraft Corporation Model 1900D Airliner Structural Inspection Manual, Part Number 129–590000–65E5, dated May 1, 2013. pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 (h) Repair If any cracks are found during any of the inspections required in paragraph (g) of this AD, to include all subparagraphs, before further flight, you must contact Beechcraft Corporation to obtain repair instructions approved by the Wichita Aircraft Certification Office (ACO) specifically for compliance with this AD and incorporate those instructions. You can find contact information for Beechcraft Corporation in paragraph (k)(1) of this AD. (i) Special Flight Permit If cracks are found during any of the inspections required in paragraph (g) of this AD, to include all subparagraphs, the FAA may allow a one-time special flight permit to a repair facility depending on the cracking found. You must contact Beechcraft Corporation and provide them with crack detail information for them to determine residual strength of the airplane before applying to the FAA for a special flight permit. You can find contact information for Beechcraft Corporation in paragraph (k)(1) of this AD. (j) 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 VerDate Mar<15>2010 13:35 Aug 26, 2013 Jkt 229001 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 (1) For more information about this AD, contact Paul Chapman, Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946–4152; fax: (316) 946–4107; email: paul.chapman@ faa.gov. (2) For service information identified in this AD, contact Beechcraft Corporation at address: 10511 E. Central, Wichita, Kansas 67206; phone: (800) 429–5372 or (316) 676– 3140; Internet: http://www.beechcraft.com/ customer_support/contact_us/. You may review copies of the 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. Issued in Kansas City, Missouri, on August 20, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–20853 Filed 8–26–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0702; Directorate Identifier 2012–NM–181–AD] RIN 2120–AA64 Airworthiness Directives; 328 Support Services GmbH (Type Certificate Previously Held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directive (AD) 2008–14– 16 that applies to certain 328 Support Services GmbH (Type Certificate Previously Held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328– 100 and 328–300 airplanes. AD 2008– 14–16 currently requires installing warning placards on the inside of the passenger door and service doors and modifying the hinge supports and SUMMARY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 support struts of the passenger doors. Since we issued AD 2008–14–16, we received reports that certain fasteners, which were installed as part of the modification, are the wrong length. This proposed AD would require replacing the fasteners which were installed as part of the modification with new fasteners of the correct length, adds new airplanes, and removes one airplane. We are proposing this AD to prevent incidents of inadvertent opening and possible detachment of a passenger door in-flight, resulting in damage to airframe and systems and loss of control of the airplane. DATES: We must receive comments on this proposed AD by October 11, 2013. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact 328 Support Services GmbH, Global Support Center, P.O. Box 1252, D–82231 Wessling, Federal Republic of Germany; telephone +49 8153 88111 6666; fax +49 8153 88111 6565; email gsc.op@ 328support.de; Internet http:// www.328support.de. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, E:\FR\FM\27AUP1.SGM 27AUP1

Agencies

[Federal Register Volume 78, Number 166 (Tuesday, August 27, 2013)]
[Proposed Rules]
[Pages 52870-52872]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-20853]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

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. 78, No. 166 / Tuesday, August 27, 2013 / 
Proposed Rules

[[Page 52870]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0753; Directorate Identifier 2013-CE-025-AD]
RIN 2120-AA64


Airworthiness Directives; Beechcraft Corporation Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Beechcraft Corporation (type certificate previously held by 
Hawker Beechcraft Corporation) Models 1900, 1900C, and 1900D airplanes. 
This proposed AD was prompted by reports of cracking in the front spar 
cap angles and hat section structure of the vertical stabilizer. This 
proposed AD would require inspections of the vertical stabilizer spar 
angles and hat section for cracks with corrective actions as necessary. 
We are proposing this AD to correct the unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by October 11, 
2013.

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.
    For service information identified in this proposed AD, contact 
Beechcraft Corporation at address: 10511 E. Central, Wichita, Kansas 
67206; phone: (800) 429-5372 or (316) 676-3140; Internet: http://www.beechcraft.com/customer_support/contact_us/. You may review 
copies of the 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 
100, Wichita, Kansas 67209; phone: (316) 946-4152; fax: (316) 946-4107; 
email: paul.chapman@faa.gov.

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-2013-0753; 
Directorate Identifier 2013-CE-025-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 were notified by Beechcraft Corporation of cracks found in the 
vertical stabilizer structure of Models 1900, 1900C, and 1900D 
airplanes. Out of 140 airplanes inspected, 56 cracks have been found. 
This condition, if not corrected, could lead to structural failure of 
the vertical stabilizer and result in loss of control.

Relevant Service Information

    We reviewed Hawker Beechcraft Mandatory Service Bulletin SB 55-
4114, dated August 2012; Hawker Beechcraft Corporation Model 1900/1900C 
Airliner Structural Inspection Manual, Part Number 98-30937G2, dated 
May 1, 2013; and Beechcraft Corporation Model 1900D Airliner Structural 
Inspection Manual, Part Number 129-590000-65E5, dated May 1, 2013. The 
service information describes procedures for visually inspecting the 
vertical stabilizer spar angles and hat section.

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.

Proposed AD Requirements

    This proposed AD would require doing visual inspections of the 
vertical stabilizer spar angles and hat section for cracks and taking 
corrective actions as necessary.

Costs of Compliance

    We estimate that this proposed AD affects 400 airplanes.
    We estimate the following costs to comply with this proposed AD:

[[Page 52871]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
              Action                     Labor cost            Parts cost           product         operators
----------------------------------------------------------------------------------------------------------------
Visual inspection of the vertical   1.5 work-hours x $85  Not applicable......         $127.50          $51,000
 stabilizer spar angles and hat      per hour = $127.50.
 section.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs 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 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair of the spar cap (right hand or left     30 work-hours x $85 per hour =             $600           $3,150
 hand).                                         $2,550.
----------------------------------------------------------------------------------------------------------------

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):

Beechcraft Corporation (Type Certificate Previously Held by Hawker 
Beechcraft Corporation): Docket No. FAA-2013-0753; Directorate 
Identifier 2013-CE-025-AD.

(a) Comments Due Date

    We must receive comments by October 11, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the following Beechcraft Corporation 
airplanes, certificated in any category:

------------------------------------------------------------------------
                Model                              Serial No.
------------------------------------------------------------------------
1900.................................  UA-3.
1900C................................  UB-1 through UB-74, UC-1 through
                                        UC-174-6.
1900C (C-12J)........................  UD-1 through UD-6.
1900D................................  UE-1 through UE-439.
------------------------------------------------------------------------

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by reports of cracking in the front spar 
cap angles and hat section of the vertical stabilizer structure. We 
are issuing this AD to detect and correct cracking in the vertical 
stabilizer structure, which could lead to structural failure of the 
vertical stabilizer and result in loss of control.

(f) Compliance

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

(g) Visual Inspections

    (1) For all airplanes: Within the next 600 hours time-in-service 
(TIS) after the effective date of this AD, inspect part number (P/N) 
101-640011-3/-4 spar angles and P/N 114-640000-25/-26 hat section 
for cracks following the Accomplishment Instructions in paragraph 
3.A. of Hawker Beechcraft Mandatory Service Bulletin SB 55-4114, 
dated August 2012.
    (2) For Models 1900 and 1900C airplanes: Within 1,200 hours TIS 
after the initial inspection required in paragraph (g)(1) of this AD 
or within 2 years after the initial inspection required in paragraph 
(g)(1) of this AD, whichever occurs first, and repetitively 
thereafter at intervals not to exceed 1,200 hours TIS or 2 years, 
whichever occurs first, inspect P/N 101-640011-3 and P/N 101-640011-
4 spar cap angles for cracks. Follow Procedure 8 under Vertical 
Stabilizer in the ``I'' Check Procedures of Hawker Beechcraft 
Corporation Model 1900/1900C Airliner Structural Inspection Manual, 
Part Number 98-30937G2, dated May 1, 2013.
    (3) For Models 1900 and 1900C airplanes: Within 1,200 hours TIS 
after the initial inspection required in paragraph (g)(1) of this AD 
or within 2 years after the initial inspection required in paragraph 
(g)(1) of this AD, whichever occurs first, and repetitively 
thereafter at intervals not to exceed 1,200 hours TIS or 2 years, 
whichever occurs first, inspect P/N 114-640000-25 and P/N 114-

[[Page 52872]]

640000-26 hat section for cracks. Follow Procedure 9 under Vertical 
Stabilizer in the ``I'' Check Procedures of Hawker Beechcraft 
Corporation Model 1900/1900C Airliner Structural Inspection Manual, 
Part Number 98-30937G2, dated May 1, 2013.
    (4) For Model 1900D airplanes: Within 1,200 hours TIS after the 
initial inspection required in paragraph (g)(1) of this AD or within 
2 years after the initial inspection required in paragraph (g)(1) of 
this AD, whichever occurs first, and repetitively thereafter at 
intervals not to exceed 1,200 hours TIS or 2 years, whichever occurs 
first, inspect P/N 101-640011-3 and P/N 101-640011-4 spar cap angles 
for cracks. Follow Procedure 6.b. under Vertical Stabilizer Canted 
Stabilizer Station (CSS 69.184 through VSS 91.10) in the ``I'' Check 
Procedures of Beechcraft Corporation Model 1900D Airliner Structural 
Inspection Manual, Part Number 129-590000-65E5, dated May 1, 2013.
    (5) For Model 1900D airplanes: Within 1,200 hours TIS after the 
initial inspection required in paragraph (g)(1) of this AD or within 
2 years after the initial inspection required in paragraph (g)(1) of 
this AD, whichever occurs first, and repetitively thereafter at 
intervals not to exceed 1,200 hours TIS or 2 years, whichever occurs 
first, inspect P/N 114-640000-25 and P/N 114-640000-26 hat section 
for cracks. Follow Procedure 6.c. under Vertical Stabilizer Canted 
Stabilizer Station (CSS 69.184 through VSS 91.10) in the ``I'' Check 
Procedures of Beechcraft Corporation Model 1900D Airliner Structural 
Inspection Manual, Part Number 129-590000-65E5, dated May 1, 2013.

(h) Repair

    If any cracks are found during any of the inspections required 
in paragraph (g) of this AD, to include all subparagraphs, before 
further flight, you must contact Beechcraft Corporation to obtain 
repair instructions approved by the Wichita Aircraft Certification 
Office (ACO) specifically for compliance with this AD and 
incorporate those instructions. You can find contact information for 
Beechcraft Corporation in paragraph (k)(1) of this AD.

(i) Special Flight Permit

    If cracks are found during any of the inspections required in 
paragraph (g) of this AD, to include all subparagraphs, the FAA may 
allow a one-time special flight permit to a repair facility 
depending on the cracking found. You must contact Beechcraft 
Corporation and provide them with crack detail information for them 
to determine residual strength of the airplane before applying to 
the FAA for a special flight permit. You can find contact 
information for Beechcraft Corporation in paragraph (k)(1) of this 
AD.

 (j) 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 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

    (1) For more information about this AD, contact Paul Chapman, 
Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 
Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946-
4152; fax: (316) 946-4107; email: paul.chapman@faa.gov.
    (2) For service information identified in this AD, contact 
Beechcraft Corporation at address: 10511 E. Central, Wichita, Kansas 
67206; phone: (800) 429-5372 or (316) 676-3140; Internet: http://www.beechcraft.com/customer_support/contact_us/. You may review 
copies of the 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.

    Issued in Kansas City, Missouri, on August 20, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013-20853 Filed 8-26-13; 8:45 am]
BILLING CODE 4910-13-P