E7-18148. 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).

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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:

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 proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

DATES:

We must receive comments on this proposed AD by October 15, 2007.

ADDRESSES:

You may send comments by any of the following methods:

• DOT Docket Web Site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.
• Fax: [phone].
• 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 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

Examining the AD Docket

You may examine the AD docket on the Internet at http://dms.dot.gov;​; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone [phone]) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT:

Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: [phone]; fax: [phone].

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2007-28957; Directorate Identifier 2007-CE-069-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://dms.dot.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

The Department of Civil Aviation (DCA), which is the aviation authority for Malaysia, has issued AD No. CAM AD 001-07-2007, dated July 20, 2007 (referred to after this as “the MCAI”), 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.

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.

You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

CTRM Aviation Sdn. Bhd. has issued Mandatory Service Bulletin SB 1126, dated, July 19, 2007. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between This Proposed 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 proposed 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 proposed AD.

Costs of Compliance

Based on the service information, we estimate that this proposed AD would affect about 6 products of U.S. registry. We also estimate that it would take about 3 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour.

Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $1,440, or $240 per product.

In addition, we estimate that any necessary follow-on actions would 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 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); 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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• 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 AD:

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

Comments Due Date

(a) We must receive comments by October 15, 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 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: [phone]; fax: [phone]. 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.

Issued in Kansas City, Missouri, on September 10, 2007.

Kim Smith,

Manager, Small Airplane Directorate, Aircraft Certification Service.