Skip to Content

Rule

Airworthiness Directives; Cessna Model 750 Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

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

ACTION:

Final rule; request for comments.

SUMMARY:

The FAA is adopting a new airworthiness directive (AD) for all Cessna Model 750 airplanes. This AD requires inspecting the inboard-hinge brackets of the left and right elevators for cracking, and doing related investigative and corrective actions if necessary. This AD results from a report of cracking found on the elevator inboard-hinge brackets. We are issuing this AD to detect and correct cracking of the elevator inboard-hinge brackets, which could result in structural failure of the elevators and consequent loss of control of the airplane.

DATES:

This AD becomes effective November 22, 2006.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 22, 2006.

We must receive comments on this AD by January 8, 2007.

ADDRESSES:

Use one of the following addresses to submit comments on this AD.

  • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.
  • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.
  • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590.
  • Fax: (202) 493-2251.
  • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Contact Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277, for service information identified in this AD.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

T.N. Baktha, Aerospace Engineer, Airframe and Services Branch, ACE-118W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4155; fax (316) 946-4107.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Discussion

We have received a report indicating that, during a maintenance inspection, a crack was found in one of the lugs on the elevator inboard-hinge bracket of a Cessna Model 750 airplane; cracking was also found on the elevator inboard-hinge brackets on seven other Model 750 airplanes. The cracking was attributed to fatigue caused by excessive side loads on the bracket from the flexing of the elevator during flight. This condition, if not corrected, could result in structural failure of the elevators and consequent loss of control of the airplane.

Relevant Service Information

We have reviewed Cessna Alert Service Letter ASL750-27-21, excluding the attachment titled “Inspection Results Form” and including the attachment titled “Flight Restrictions,” dated October 13, 2006. The service letter describes procedures for performing a visual inspection of the inboard-hinge brackets of the left and right elevators. Related investigative and corrective actions include:

  • If any crack is found: Perform an eddy current inspection of the bracket(s) to confirm the crack and its length.
  • If the crack is 0.30 inch or more: Replace the bracket(s) before the next flight.
  • If the crack is less than 0.30 inch: Continued flight for repositioning of the airplane and replacement of the bracket is allowed within the restricted flight envelope included in the attachment to the service letter titled “Flight Restrictions,” for a maximum of 10 flight hours” time-in-service.

FAA's Determination and Requirements of This AD

The unsafe condition described previously is likely to exist or develop on other airplanes of the same type design. For this reason, we are issuing this AD to detect and correct cracking of the elevator inboard-hinge brackets, which could result in structural failure of the elevators and consequent loss of control of the airplane. This AD requires inspecting the inboard-hinge brackets of the left and right elevators for cracking, and doing related investigative and corrective actions if necessary; except as discussed under “Differences Between the AD and the Service Letter.” Start Printed Page 65048

Differences Between the AD and the Service Letter

While it is not our usual policy to allow flight with known cracks, to be consistent with the service letter, this AD permits further flight with cracks with certain restrictions, as specified in paragraph (g)(2) of this AD. In consideration of these restrictions and the FAA's criteria for flight with known cracking, continued flight for a maximum of 10 flight hours for repositioning of the airplane and replacement of the bracket is allowed, provided the airplane is operated in accordance with the revised flight restrictions specified in the service letter.

The procedures in the service letter refer only to a “visual inspection” for cracking of the inboard-hinge brackets. We have determined that the inspection should be described as a “general visual inspection.” Note 1 has been included in this AD to define this type of inspection.

The procedures in the service letter specify submitting a sheet related to inspection results to the manufacturer, but this AD does not require that action.

The procedures in the service letter also specify sending the elevator assembly to the manufacturer for replacement of the inboard-hinge bracket if a crack is found that is 0.30 inch or longer; however, this AD requires corrective actions be done using a method approved by us.

Interim Action

We consider this AD interim action. If final action is later identified, we may consider further rulemaking then.

FAA's Determination of the Effective Date

Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists to make this AD effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed in the ADDRESSES section. Include “Docket No. FAA-2006-26242; Directorate Identifier 2006-NM-229-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it.

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 with FAA personnel concerning this AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including 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), or you may visit http://dms.dot.gov.

Examining the Docket

You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647-5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them.

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 the 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 AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

Adoption of the Amendment

Start Amendment Part

Accordingly, under the authority delegated to me by the Administrator, the FAA amends

End Amendment Part Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

1. The authority citation for part 39 continues to read as follows:

End Amendment Part Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]
Start Amendment Part

2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD):

End Amendment Part

2006-23-05 Cessna Aircraft Company: Amendment 39-14817. Docket No. FAA-2006-26242; Directorate Identifier 2006-NM-229-AD.

Effective Date

(a) This AD becomes effective November 22, 2006.

Affected ADs

(b) None.

Applicability

(c) This AD applies to all Cessna Model 750 airplanes, certificated in any category.

Unsafe Condition

(d) This AD results from a report of cracking found on the elevator inboard-hinge brackets. We are issuing this AD to detect and correct cracking of the elevator inboard-hinge brackets, which could result in structural failure of the elevator and consequent loss of control of the airplane.

Compliance

(e) You are responsible for having the actions required by this AD performed within Start Printed Page 65049the compliance times specified, unless the actions have already been done.

Inspection

(f) After the airplane accumulates 2,500 total flight hours: Perform a general visual inspection for cracking of the inboard-hinge brackets of the left and right elevators in accordance with the Accomplishment Instructions of Cessna Alert Service Letter ASL750-27-21, dated October 13, 2006. Do the inspection before the airplane accumulates 3,000 total flight hours, or within 10 flight hours after the effective date of this AD, whichever is later.

Note 1:

For the purposes of this AD, a general visual inspection is: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”

Related Investigative and Corrective Actions

(g) If any crack is found during the inspection required by paragraph (f) of this AD: Before further flight, perform an eddy current inspection of the inboard-hinge brackets to determine the crack length, in accordance with the Accomplishment Instructions of Cessna Alert Service Letter ASL750-27-21, dated October 13, 2006; and do the actions specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, at the time specified. All corrective actions must be done using a method approved by the Manager, Wichita Aircraft Certification Office (ACO), FAA. For a replacement method to be approved by the Manager, Wichita ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD.

(1) If the crack is 0.30 inch or more: Replace the bracket before further flight.

(2) If the crack is less than 0.30 inch: Continued flight for a maximum of 10 flight hours for repositioning of the airplane and replacement of the bracket is allowed, within the restricted flight envelope included in the attachment to the service letter titled “Flight Restrictions.”

Special Flight Permits

(h) Special flight permits, as described in Section 39.23 of the Federal Aviation Regulations (14 CFR 39.23), are allowed with the limitations required by paragraph (g)(2) of this AD.

No Reporting or Return of Parts to Manufacturer

(i) Cessna Alert Service Letter ASL750-27-21, dated October 13, 2006, specifies submitting a sheet related to inspection results to the manufacturer; this AD does not include that requirement. The service letter also specifies sending the elevator assembly to the manufacturer for replacement of the inboard-hinge bracket if a crack is found that is 0.30 inch or more; however, this AD requires corrective actions be done using a method approved by us.

Alternative Methods of Compliance (AMOCs)

(j)(1) The Manager, Wichita ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19.

(2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office.

Material Incorporated by Reference

(k) You must use Cessna Alert Service Letter ASL750-27-21, excluding the attachment titled “Inspection Results Form” and including the attachment titled “Flight Restrictions,” dated October 13, 2006, 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 Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov;​ or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/​federal_​register/​code_​of_​federal_​regulations/​ibr_​locations.html.

Start Signature

Issued in Renton, Washington, on October 26, 2006.

Kalene C. Yanamura,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. E6-18659 Filed 11-6-06; 8:45 am]

BILLING CODE 4910-13-P