Airworthiness Directives; Hawker Beechcraft Model 400, 400A, and 400T Series Airplanes, 53104-53106 [E7-18048]

Download as PDF 53104 Federal Register / Vol. 72, No. 180 / Tuesday, September 18, 2007 / Rules and Regulations FAA AD Differences the FAA amends 14 CFR part 39 as follows: Note: This AD differs from the MCAI and/ or service information as follows: No differences. PART 39—AIRWORTHINESS DIRECTIVES Other FAA AD Provisions 1. The authority citation for part 39 continues to read as follows: I (d) Air Transport Association (ATA) of America Code 32: Landing Gear. (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Reason Related Information (e) The mandatory continuing airworthiness information (MCAI) states: Further to cases of parking brake loss at the gate, a pressure switch system had been introduced on some A300–600 aircraft. The aim of this modification was to recover pedals braking authority if parking brake is not efficient, without having to set the parking brake handle to OFF. However, it appears that in case of failure of the pressure switch system, there is the risk of double (normal and alternate) pressurization of the brakes potentially leading to undetected residual braking, which may lead to a loss of performances of the aircraft at Take-Off. This new AD requires accomplishment of a wiring modification that will inhibit the effect of modifications 12088 and 12403. The loss of performance could result in runway overrun or impact with obstacles or terrain during takeoff. (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2007– 0068, dated March 14, 2007; and Airbus Service Bulletin A300–32–6100, dated September 18, 2006; for related information. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2007–19–04 Airbus: Amendment 39–15194. Docket No. FAA–2007–28372; Directorate Identifier 2007–NM–080–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 23, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A300F4–605R and A300F4–622R airplanes; certificated in any category; all serial numbers; on which Airbus Modifications 12088 and 12403 have been embodied during production, or which incorporated Airbus Service Bulletin A300–32–6085 in service, except airplanes on which Airbus Modification 12618 has been embodied during production, or which incorporated Airbus Service Bulletin A300–32–6100 in service. Subject mstockstill on PROD1PC66 with RULES Actions and Compliance (f) Within 3 months after the effective date of this AD unless already done: Modify the wiring in the right electronics rack 90VU (volt unit), in accordance with the instructions of Airbus Service Bulletin A300– 32–6100, dated September 18, 2006. VerDate Aug<31>2005 18:27 Sep 17, 2007 Jkt 211001 Material Incorporated by Reference (i) You must use Airbus Service Bulletin A300–32–6100, dated September 18, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Issued in Renton, Washington, on August 31, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–18050 Filed 9–17–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28308; Directorate Identifier 2007–NM–016–AD; Amendment 39–15195; AD 2007–19–05] RIN 2120–AA64 Airworthiness Directives; Hawker Beechcraft Model 400, 400A, and 400T Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Model 400, 400A, and 400T series airplanes. This AD requires modifying the attachment fasteners on the engine cowling panels. 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. DATES: This AD becomes effective October 23, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 23, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. Contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67206, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: William Griffith, Aerospace Engineer, E:\FR\FM\18SER1.SGM 18SER1 Federal Register / Vol. 72, No. 180 / Tuesday, September 18, 2007 / Rules and Regulations 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: Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located on the ground floor of the West Building at the DOT street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Raytheon (Beech) Model 400, 400A, and 400T series airplanes. That NPRM was published in the Federal Register on May 29, 2007 (72 FR 29446). That NPRM proposed to require modifying the attachment fasteners on the engine cowling panels. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM or on the determination of the cost to the public. Explanation of Change to Applicability We have revised the applicability of the existing AD to match the most recent type certificate data sheet for the affected models. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. mstockstill on PROD1PC66 with RULES Costs of Compliance There are about 757 airplanes of the affected design in the worldwide fleet. This AD affects about 575 airplanes of U.S. registry. The required actions take about 10 work hours per airplane, at an average labor rate of $80 per work hour. Required parts cost about $400 per airplane. Based on these figures, the estimated cost of this AD for U.S. operators is $690,000, or $1,200 per airplane. VerDate Aug<31>2005 18:27 Sep 17, 2007 Jkt 211001 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 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. 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, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 53105 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2007–19–05 Hawker Beechcraft Corporation (Formerly Raytheon Aircraft Company): Amendment 39– 15195. Docket No. FAA–2007–28308; Directorate Identifier 2007–NM–016–AD. Effective Date (a) This AD becomes effective October 23, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Hawker Beechcraft 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, 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. Material Incorporated by Reference (h) You must use Raytheon Service Bulletin SB 54–3788, dated December 2006, E:\FR\FM\18SER1.SGM 18SER1 53106 Federal Register / Vol. 72, No. 180 / Tuesday, September 18, 2007 / Rules and Regulations to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67206, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal-register/ cfr/ibr-locations.html. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25239; Directorate Identifier 2006–NE–23–AD; Amendment 39– 15196; AD 2007–19–06] RIN 2120–AA64 Airworthiness Directives; General Electric Company Aircraft Engine Group (GEAE) CF6–45A Series, CF6– 50A, CF6–50C Series and CF6–50E Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. mstockstill on PROD1PC66 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GEAE CF6–45A, –45A2, –50A, –50C, –50CA, –50C1, –50C2, –50C2B, –50C2D, –50C2F, –50C2R, –50E, –50E1, – 50E2, and –50E2B turbofan engines. This AD requires replacing the compressor discharge pressure (CDP) restoring spring assembly on certain main engine controls (MECs) or re-marking MECs that already incorporate GEAE Service Bulletin (SB) No. CF6–50 S/B 73–0119, dated March 21, 2005. This AD results from reports of five events involving fractured CDP restoring spring assemblies. We are issuing this AD to prevent loss of engine thrust control that could lead to loss of control of the airplane. DATES: This AD becomes effective October 23, 2007. The Director of the Federal Register approved the incorporation by reference of certain VerDate Aug<31>2005 18:27 Sep 17, 2007 Jkt 211001 Costs of Compliance Examining the AD Docket Issued in Renton, Washington, on August 31, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–18048 Filed 9–17–07; 8:45 am] publications listed in the regulations as of October 23, 2007. ADDRESSES: You can get the service information identified in this AD from General Electric Company via GE– Aviation, Attn: Distributions, 111 Merchant St., Room 230, Cincinnati, Ohio 45246; telephone (513) 552–3272; fax (513) 552–3329. The Docket Operations office is located at U.S. Department of Transportation, Docket Operations, M– 30, West Building, Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7773; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GEAE CF6–45A, –45A2, –50A, –50C, –50CA, –50C1, –50C2, –50C2B, –50C2D, –50C2F, –50C2R, –50E, –50E1, –50E2, and –50E2B turbofan engines. We published the proposed AD in the Federal Register on May 31, 2007 (74 FR 30300). That action proposed to require replacing the CDP restoring spring assembly on certain MECs and re-marking MECs that already incorporate GEAE SB No. CF6–50 S/B 73–0119, dated March 21, 2005 or GEAE SB No. CF6–50 S/B 73–0119, Revision 01, dated May 26, 2006. Regulatory Findings You may examine the AD docket on the Internet at https://dms.dot.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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. We have 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 summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. The commenters support the proposal. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 We estimate that this proposed AD would affect 756 GEAE CF6–45A, –50C, and –50E series turbofan engines installed on airplanes of U.S. registry. We also estimate that it would take about 40 work-hours per engine to perform the proposed actions, and that the average labor rate is $80 per workhour. Required parts would cost about $1,787 per engine. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $3,770,172. 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. E:\FR\FM\18SER1.SGM 18SER1

Agencies

[Federal Register Volume 72, Number 180 (Tuesday, September 18, 2007)]
[Rules and Regulations]
[Pages 53104-53106]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-18048]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28308; Directorate Identifier 2007-NM-016-AD; 
Amendment 39-15195; AD 2007-19-05]
RIN 2120-AA64


Airworthiness Directives; Hawker Beechcraft Model 400, 400A, and 
400T Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Hawker Beechcraft Model 400, 400A, and 400T series airplanes. 
This AD requires modifying the attachment fasteners on the engine 
cowling panels. 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.

DATES: This AD becomes effective October 23, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of October 23, 
2007.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue, SE., Washington, DC.
    Contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, 
Kansas 67206, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: William Griffith, Aerospace Engineer,

[[Page 53105]]

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:

Examining the Docket

    You may examine the AD docket on the Internet at https://dms.dot.gov 
or in person at the Docket Operations office between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The Docket Operations 
office (telephone (800) 647-5527) is located on the ground floor of the 
West Building at the DOT street address stated in the ADDRESSES 
section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Raytheon 
(Beech) Model 400, 400A, and 400T series airplanes. That NPRM was 
published in the Federal Register on May 29, 2007 (72 FR 29446). That 
NPRM proposed to require modifying the attachment fasteners on the 
engine cowling panels.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the NPRM or on the 
determination of the cost to the public.

Explanation of Change to Applicability

    We have revised the applicability of the existing AD to match the 
most recent type certificate data sheet for the affected models.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD with the 
change described previously. We have determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Costs of Compliance

    There are about 757 airplanes of the affected design in the 
worldwide fleet. This AD affects about 575 airplanes of U.S. registry. 
The required actions take about 10 work hours per airplane, at an 
average labor rate of $80 per work hour. Required parts cost about $400 
per airplane. Based on these figures, the estimated cost of this 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 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. 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2007-19-05 Hawker Beechcraft Corporation (Formerly Raytheon Aircraft 
Company): Amendment 39-15195. Docket No. FAA-2007-28308; Directorate 
Identifier 2007-NM-016-AD.

Effective Date

    (a) This AD becomes effective October 23, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Hawker Beechcraft 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, 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.

Material Incorporated by Reference

    (h) You must use Raytheon Service Bulletin SB 54-3788, dated 
December 2006,

[[Page 53106]]

to perform the actions that are required by this AD, unless the AD 
specifies otherwise. The Director of the Federal Register approved 
the incorporation by reference of this document in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. Contact Hawker Beechcraft 
Corporation, 9709 East Central, Wichita, Kansas 67206, for a copy of 
this service information. You may review copies at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 31, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-18048 Filed 9-17-07; 8:45 am]
BILLING CODE 4910-13-P

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