Airworthiness Directives; CTRM Aviation Sdn. Bhd. (Formerly Eagle Aircraft (Malaysia) Sdn. Bhd.) Model Eagle 150B Airplanes, 62560-62562 [E7-21667]

Download as PDF 62560 Federal Register / Vol. 72, No. 214 / Tuesday, November 6, 2007 / Rules and Regulations 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 this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 the NPRM, 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. 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 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I mstockstill on PROD1PC66 with RULES 2007–23–04 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39–15250. Docket No. FAA–2007–29066; Directorate Identifier 2007–NM–147–AD. Affected ADs (b) None. VerDate Aug<31>2005 16:30 Nov 05, 2007 Jkt 214001 Reason (e) The mandatory continuing airworthiness information (MCAI) states: It has been discovered in several cases that clamp bolts of the elevator spring tab mechanism were not installed in the correct orientation. Bolts have been found installed with bolt heads on the lower position and in two cases, some bolts, nuts and washers [hardware] were found to be loose or missing. Detachment of an elevator spring tab mechanism clamp bolt could lead to jamming of the elevator control system and reduced controllability of the aircraft. The corrective action is a one-time inspection of the left- and right-hand elevator spring tab mechanism hardware for correct installation, and prior to further flight, installing new hardware for any hardware that is incorrectly installed. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 12 months after the effective date of this AD: Carry out a one-time inspection of the left- and right-hand elevator spring tab mechanism hardware for correct installation according to the Accomplishment Instructions of Bombardier Service Bulletin 8–27–106, dated February 7, 2006. (2) If any hardware is found incorrectly installed during the inspection required by paragraph (f)(1) of this AD, prior to further flight, install new hardware according to the Accomplishment Instructions of Bombardier Service Bulletin 8–27–106, dated February 7, 2006. Note: This AD differs from the MCAI and/ or service information as follows: No differences. I Effective Date (a) This airworthiness directive (AD) becomes effective December 11, 2007. Subject (d) Air Transport Association (ATA) of America Code 27: Flight controls. FAA AD Differences PART 39—AIRWORTHINESS DIRECTIVES § 39.13 Applicability (c) This AD applies to Bombardier Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes; certificated in any category; serial numbers 003 through 611 inclusive. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, 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: Dan Parrillo, Aerospace Engineer, Systems and Flight Test Branch, ANE–172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7305; fax (516) 794– 5531. 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. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 (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. Related Information (h) Refer to MCAI Canadian Airworthiness Directive CF–2007–08, dated June 4, 2007, and Bombardier Service Bulletin 8–27–106, dated February 7, 2006, for related information. Material Incorporated by Reference (i) You must use Bombardier Service Bulletin 8–27–106, dated February 7, 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 Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. (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. Issued in Renton, Washington, on October 27, 2007. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–21672 Filed 11–5–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28957 Directorate Identifier 2007–CE–069–AD; Amendment 39–15252; AD 2007–23–06] RIN 2120–AA64 Airworthiness Directives; CTRM Aviation Sdn. Bhd. (Formerly Eagle Aircraft (Malaysia) Sdn. Bhd.) Model Eagle 150B Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: E:\FR\FM\06NOR1.SGM 06NOR1 Federal Register / Vol. 72, No. 214 / Tuesday, November 6, 2007 / Rules and Regulations ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: An operator has reported severe exfoliation corrosion on Wing/Canard Flap Hinges, P/N 5731D01–16 (middle and outboard hinges) on his Eagle 150B. The corrosion has been detected during 100-hour inspection. The aircraft has accumulated more than 1000 flight hours. The corrosion is so severe that one of the Flap Hinges thickness has been reduced by 50%. The corrosion is not easily detected because the Flap Hinge is sandwiched between the Flap Hinge Support Bracket P/N 5731D01–01. The failure of the hinge bracket may result in disintegration of flap/canard wing thus leading to loss of control, with catastrophic consequences. mstockstill on PROD1PC66 with RULES We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 11, 2007. On December 11, 2007, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at Document Management Facility, 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: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on September 14, 2007 (72 FR 52519). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: An operator has reported severe exfoliation corrosion on Wing/Canard Flap Hinges, P/N 5731D01–16 (middle and outboard hinges) on his Eagle 150B. The corrosion has been detected during 100-hour inspection. The VerDate Aug<31>2005 16:30 Nov 05, 2007 Jkt 214001 aircraft has accumulated more than 1000 flight hours. The corrosion is so severe that one of the Flap Hinges thickness has been reduced by 50%. The corrosion is not easily detected because the Flap Hinge is sandwiched between the Flap Hinge Support Bracket P/N 5731D01–01. The failure of the hinge bracket may result in disintegration of flap/canard wing thus leading to loss of control, with catastrophic consequences. 62561 We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. 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. Conclusion Regulatory Findings We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. 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 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. Comments Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance Based on the service information, we estimate that this AD will affect about 6 products of U.S. registry. We also estimate that it will take about 3 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the AD to U.S. operators to be $1,440, or $240 per product. In addition, we estimate that any necessary follow-on actions will take about 4 work-hours and require parts costing $226, for a cost of $546 per product. We have no way of determining the number of products that may need these actions. Examining the AD Docket Authority for This Rulemaking Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 You may examine the AD docket on the Internet at https:// 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 the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, I E:\FR\FM\06NOR1.SGM 06NOR1 62562 Federal Register / Vol. 72, No. 214 / Tuesday, November 6, 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 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 2007–23–06 CTRM Aviation Sdn. Bhd. (Formerly Eagle Aircraft (Malaysia) Sdn. Bhd.): Amendment 39–15252; Docket No. FAA–2007–28957; Directorate Identifier 2007–CE–069–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 11, 2007. Affected ADs (b) None. Applicability (c) This AD affects Model Eagle 150B airplanes, all serial numbers, that are certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 57: Wings. Reason (e) The mandatory continuing airworthiness information (MCAI) states: An operator has reported severe exfoliation corrosion on Wing/Canard Flap Hinges, P/N 5731D01–16 (middle and outboard hinges) on his Eagle 150B. The corrosion has been detected during 100-hour inspection. The aircraft has accumulated more than 1000 flight hours. The corrosion is so severe that one of the Flap Hinges thickness has been reduced by 50%. The corrosion is not easily detected because the Flap Hinge is sandwiched between the Flap Hinge Support Bracket P/N 5731D01–01. The failure of the hinge bracket may result in disintegration of flap/canard wing thus leading to loss of control, with catastrophic consequences. mstockstill on PROD1PC66 with RULES The MCAI requires you to visually inspect the flap hinges and flap hinge support brackets for any corrosion. You are to take corrective action if you find any corrosion. Actions and Compliance (f) Unless already done, do the following actions: (1) Within the next 25 hours time-inservice (TIS) after December 11, 2007 (the effective date of this AD), inspect the flap hinges and flap hinge support brackets for any corrosion, following CTRM Aviation Mandatory Service Bulletin SB 1126, dated July 19, 2007. (2) Before further flight, if you find any corrosion as a result of any inspection required by paragraph (f)(1) of this AD, take corrective action following CTRM Aviation Mandatory Service Bulletin SB 1126, dated July 19, 2007. VerDate Aug<31>2005 16:30 Nov 05, 2007 Jkt 214001 (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. 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 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI Department of Civil Aviation Malaysia AD No. CAM AD 001–07– 2007, dated July 20, 2007; and CTRM Aviation Mandatory Service Bulletin SB 1126, dated July 19, 2007, for related information. Material Incorporated by Reference (i) You must use CTRM Aviation Mandatory Service Bulletin SB 1126, dated July 19, 2007, 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 CTRM Aviation Sdn. Bhd. (formerly known as Eagle Aircraft Sdn. Bhd.), Locked Bag 1028, Pejabat Pos Besar Melaka, 75150 Melaka, Malaysia; telephone: 06 317 1007; fax: 06 317 7023. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Issued in Kansas City, Missouri, on October 29, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–21667 Filed 11–5–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–29064; Directorate Identifier 2007–NM–128–AD; Amendment 39–15249; AD 2007–23–03] RIN 2120–AA64 Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: One Fokker 100 (F28 Mark 0100) operator reported that during maintenance in the APU (auxiliary power unit) compartment, a disconnected nut was discovered on one of the shuttle valves in the deployment lines of the engine fire-extinguishing system. An additional check by the operator revealed that on more aircraft in its fleet, the nuts of the shuttle valves were incorrectly tightened. This condition, if not corrected, could result in failure or deteriorated functioning of the engine fire-extinguishing system in case of an engine fire. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective December 11, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 11, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.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. E:\FR\FM\06NOR1.SGM 06NOR1

Agencies

[Federal Register Volume 72, Number 214 (Tuesday, November 6, 2007)]
[Rules and Regulations]
[Pages 62560-62562]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-21667]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28957 Directorate Identifier 2007-CE-069-AD; 
Amendment 39-15252; AD 2007-23-06]
RIN 2120-AA64


Airworthiness Directives; CTRM Aviation Sdn. Bhd. (Formerly Eagle 
Aircraft (Malaysia) Sdn. Bhd.) Model Eagle 150B Airplanes

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

[[Page 62561]]


ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    An operator has reported severe exfoliation corrosion on Wing/
Canard Flap Hinges, P/N 5731D01-16 (middle and outboard hinges) on 
his Eagle 150B. The corrosion has been detected during 100-hour 
inspection. The aircraft has accumulated more than 1000 flight 
hours. The corrosion is so severe that one of the Flap Hinges 
thickness has been reduced by 50%. The corrosion is not easily 
detected because the Flap Hinge is sandwiched between the Flap Hinge 
Support Bracket P/N 5731D01-01.

    The failure of the hinge bracket may result in disintegration of 
flap/canard wing thus leading to loss of control, with catastrophic 
consequences.

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective December 11, 2007.
    On December 11, 2007, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in this 
AD.

ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov or in person at Document Management Facility, 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: Karl Schletzbaum, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on September 14, 2007 
(72 FR 52519). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    An operator has reported severe exfoliation corrosion on Wing/
Canard Flap Hinges, P/N 5731D01-16 (middle and outboard hinges) on 
his Eagle 150B. The corrosion has been detected during 100-hour 
inspection. The aircraft has accumulated more than 1000 flight 
hours. The corrosion is so severe that one of the Flap Hinges 
thickness has been reduced by 50%. The corrosion is not easily 
detected because the Flap Hinge is sandwiched between the Flap Hinge 
Support Bracket P/N 5731D01-01.
    The failure of the hinge bracket may result in disintegration of 
flap/canard wing thus leading to loss of control, with catastrophic 
consequences.

Comments

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

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the AD.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 6 products of U.S. registry. We also estimate that it will 
take about 3 work-hours per product to comply with the basic 
requirements of this AD. The average labor rate is $80 per work-hour.
    Based on these figures, we estimate the cost of the AD to U.S. 
operators to be $1,440, or $240 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 4 work-hours and require parts costing $226, for a cost of 
$546 per product. We have no way of determining the number of products 
that may need these actions.

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 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 on the Internet at https://
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 the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone (800) 647-5527) is 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,

[[Page 62562]]

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 FAA amends Sec.  39.13 by adding the following new AD:

2007-23-06 CTRM Aviation Sdn. Bhd. (Formerly Eagle Aircraft 
(Malaysia) Sdn. Bhd.): Amendment 39-15252; Docket No. FAA-2007-
28957; Directorate Identifier 2007-CE-069-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
11, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD affects Model Eagle 150B airplanes, all serial 
numbers, that are certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    An operator has reported severe exfoliation corrosion on Wing/
Canard Flap Hinges, P/N 5731D01-16 (middle and outboard hinges) on 
his Eagle 150B. The corrosion has been detected during 100-hour 
inspection. The aircraft has accumulated more than 1000 flight 
hours. The corrosion is so severe that one of the Flap Hinges 
thickness has been reduced by 50%. The corrosion is not easily 
detected because the Flap Hinge is sandwiched between the Flap Hinge 
Support Bracket P/N 5731D01-01.

    The failure of the hinge bracket may result in disintegration of 
flap/canard wing thus leading to loss of control, with catastrophic 
consequences.

The MCAI requires you to visually inspect the flap hinges and flap 
hinge support brackets for any corrosion. You are to take corrective 
action if you find any corrosion.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Within the next 25 hours time-in-service (TIS) after 
December 11, 2007 (the effective date of this AD), inspect the flap 
hinges and flap hinge support brackets for any corrosion, following 
CTRM Aviation Mandatory Service Bulletin SB 1126, dated July 19, 
2007.
    (2) Before further flight, if you find any corrosion as a result 
of any inspection required by paragraph (f)(1) of this AD, take 
corrective action following CTRM Aviation Mandatory Service Bulletin 
SB 1126, dated July 19, 2007.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No Differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, 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: Karl Schletzbaum, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090. 
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 (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (h) Refer to MCAI Department of Civil Aviation Malaysia AD No. 
CAM AD 001-07-2007, dated July 20, 2007; and CTRM Aviation Mandatory 
Service Bulletin SB 1126, dated July 19, 2007, for related 
information.

Material Incorporated by Reference

    (i) You must use CTRM Aviation Mandatory Service Bulletin SB 
1126, dated July 19, 2007, 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 CTRM 
Aviation Sdn. Bhd. (formerly known as Eagle Aircraft Sdn. Bhd.), 
Locked Bag 1028, Pejabat Pos Besar Melaka, 75150 Melaka, Malaysia; 
telephone: 06 317 1007; fax: 06 317 7023.
    (3) You may review copies at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 
64106; 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 Kansas City, Missouri, on October 29, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
 [FR Doc. E7-21667 Filed 11-5-07; 8:45 am]
BILLING CODE 4910-13-P