E9-3608. Airworthiness Directives; Hamilton Sundstrand Propellers Model 247F Propellers

AGENCY:

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

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

The FAA proposes to adopt a new airworthiness directive (AD) for Hamilton Sundstrand Propellers model 247F propeller assemblies with certain part number (P/N) and serial number (SN) blades. This proposed AD would require removing affected propeller blades from service. This proposed AD results from reports of blades with corrosion pits in the tulip area of the blades. We are proposing this AD to prevent cracks from developing in the tulip area of the blade, which could result in separation of the blade and possible loss of airplane control.

DATES:

We must receive any comments on this proposed AD by April 21, 2009.

ADDRESSES:

Use one of the following addresses to comment on this proposed AD.

• Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.
• Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001.
• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
• Fax: [phone].

You can get the service information identified in this proposed AD from Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, Mail Stop 1-3-AB43, Windsor Locks, CT 06096-1010; fax [phone].

FOR FURTHER INFORMATION CONTACT:

Terry Fahr, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: [e-mail]; telephone [phone]; fax [phone].

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include “Docket No. FAA-2009-0113; Directorate Identifier 2008-NE-25-AD” in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light 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 with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78).

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 [phone]) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

Discussion

We have received reports of corrosion on 6 propeller blades. A lack of adhesive and primer beyond the end of the compression wrap during manufacturing of certain serial-numbered propeller blades, P/N R817370-1, could result in corrosion pits developing in the tulip area of the propeller blade. This condition, if not corrected, could cause cracks in the tulip area, which could result in separation of the propeller blade and possible loss of airplane control.

Relevant Service Information

We have reviewed and approved the technical contents of Hamilton Sundstrand Service Bulletin 247F-61-54, Revision 1, dated January 12, 2004, that describes procedures for reworking and re-marking the blade with a new P/N.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. We are proposing this AD, which would require removing propeller blades, P/N R817370-1, with a SN listed in this proposed AD, within 30 days after the effective date of this proposed AD.

Costs of Compliance

We estimate that this proposed AD would affect 25 propellers installed on airplanes of U.S. registry. We also estimate that it would take about 128 work-hours per propeller to perform the proposed actions, and that the average labor rate is $80 per work-hour. Required parts would cost about $50 per propeller. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $257,250.

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 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 that the proposed 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. Would 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. You may get a copy of this summary at the address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Safety

The Proposed Amendment

Under the authority delegated to me by the Administrator, the Federal Aviation Administration 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:

Hamilton Sundstrand Corporation: Docket No. FAA-2009-0113; Directorate Identifier 2008-NE-25-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by April 21, 2009.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Hamilton Sundstrand model 247F series propellers with blades part number (P/N) 817370-1, serial numbers (SNs) FR2018, FR2083, FR2103, FR2108, FR2109, FR2111, FR2123, FR2178, FR2183, FR2187, FR2262, FR2276 through FR2279, FR2303, and FR2389, installed. These propellers are installed on, but not limited to, ATR-GIE Avions de Transport Regional ATR72-210 and ATR72-210E airplanes.

Unsafe Condition

(d) This AD results from reports of blades with corrosion pits in the tulip area of the blades. We are issuing this AD to prevent cracks from developing in the tulip area of the blade, which could result in separation of the blade and possible loss of airplane control.

Compliance

(e) You are responsible for having the actions required by this AD performed within 30 days after the effective date of this AD.

Removing Blades P/N R817370-1

(f) Remove blades P/N 817370-1, SNs FR2018, FR2083, FR2103, FR2108, FR2109, FR2111, FR2123, FR2178, FR2183, FR2187, FR2262, FR2276 through FR2279, FR2303, and FR2389.

Alternative Methods of Compliance

(g) The Manager, Boston Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19.

Related Information

(h) Contact Terry Fahr, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: [e-mail]; telephone [phone]; fax [phone], for more information about this AD.

(i) Hamilton Sundstrand Service Bulletin 247F-61-54, Revision 1, dated January 12, 2004, pertains to the subject of this AD. Contact Hamilton Sundstrand Propeller Technical Team, One Hamilton Road, Mail Stop 1-3-AB43, Windsor Locks, CT 06096-1010; fax [phone], for a copy of this service information.

Issued in Burlington, Massachusetts, on February 11, 2009.

Peter A. White,

Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.