Airworthiness Directives; Saab Model SAAB 2000 Series Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires measuring the torque of the adjustable pin in the rear attachment of the intermediate strut for both engines, and retorquing the adjustable pins to the correct torque value. This action is necessary to prevent long-term damage to the engine mounting structure (EMS), and loss of redundancy on the EMS, which could result in possible separation of an engine from the airplane, reduced controllability of the airplane, and injury to persons or property on the ground. This action is intended to address the identified unsafe condition.

DATES:

Effective April 30, 2004.

The incorporation by reference of a certain publication listed in the regulations is approved by the Director of the Federal Register as of April 30, 2004.

ADDRESSES:

The service information referenced in this AD may be obtained from Saab Aircraft AB, SAAB Aircraft Product Support, S-581.88, Linköping, Sweden. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Rosanne Ryburn, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4057; telephone (425) 227-2139; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Saab Model SAAB 2000 series airplanes was published in the Federal Register on January 5, 2004 (69 FR 293). That action proposed to require measuring the torque of the adjustable pin in the rear attachment of the intermediate strut for both engines, and retorquing the adjustable pins to the correct torque value.

Comments

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public.

Conclusion

The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

Cost Impact

The FAA estimates that 3 airplanes of U.S. registry will be affected by this AD, that it will take approximately 2 work hours per airplane to accomplish the required actions, and that the average labor rate is $65 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $390, or $130 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.

Regulatory Impact

The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Incorporation by reference
• Safety

Adoption of the Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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.

2. Section 39.13 is amended by adding the following new airworthiness directive:

2004-06-14  Saab Aircraft AB: Amendment 39-13540. Docket 2003-NM-115-AD.

Applicability: Model SAAB 2000 series airplanes, serial numbers -004 through -063 inclusive; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent long-term damage to the engine mounting structure (EMS), and loss of redundancy on the EMS, which could result in possible separation of an engine from the airplane, reduced controllability of the airplane, and injury to persons or property on the ground, accomplish the following:

Service Bulletin References

(a) The following information pertains to the service bulletin referenced in this AD:

(1) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Saab Service Bulletin 2000-71-014, dated January 23, 2003.

(2) Although the service bulletin specifies to submit certain information to the manufacturer, this AD does not include such a requirement.

Torque Check

(b) Within 3 months after the effective date of this AD: Measure the torque of the adjustable pin in the rear attachment of the intermediate strut for both engines, in accordance with the inspection requirements and torque values in the service bulletin.

Retorque

(c) Retorque the adjustable pin in the intermediate strut rear attachment of the EMS to the correct torque value, in accordance with the service bulletin.

Alternative Methods of Compliance

(d) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, is authorized to approve alternative methods of compliance for this AD.

Incorporation by Reference

(e) The actions shall be done in accordance with Saab Service Bulletin 2000-71-014, dated January 23, 2003. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Saab Aircraft AB, SAAB Aircraft Product Support, S-581.88, Linköping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Note 1:

The subject of this AD is addressed in Swedish airworthiness directive 1-183, dated January 23, 2003.

Effective Date

(f) This amendment becomes effective on April 30, 2004.