Airworthiness directives: Saab,
[Federal Register: July 22, 1999 (Volume 64, Number 140)]
[Rules and Regulations]
[Page 39396-39398]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22jy99-2]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-350-AD; Amendment 39-11232; AD 99-15-12]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB 2000 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes. This action requires repetitive detailed inspections to detect looseness or gap of the press fit bushing installation of the actuator fittings of the aileron trim tabs, and eventual replacement of the bushings with new, staked bushings. Accomplishment of such replacement terminates the repetitive inspections. This action also provides for an optional temporary preventive action, which, if accomplished, would terminate the repetitive inspections until the terminating action is accomplished. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent looseness or gap of the bushings. In the event of failure of the redundant trim tab actuator, such looseness or gap of the bushings could lead to trim tab flutter and consequent structural failure of the trim tab and reduced controllability of the airplane.
DATES: Effective August 6, 1999.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 6, 1999.
Comments for inclusion in the Rules Docket must be received on or before August 23, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 98-NM-350-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from Saab Aircraft AB, SAAB Aircraft Product Support, S-581.88, Linkoping, Sweden. This information may be examined 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.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Luftfartsverket (LFV), which is the airworthiness authority for Sweden, notified the FAA that an unsafe condition may exist on certain Saab Model SAAB 2000 series airplanes. The LFV advises that a failure of a bushing of the flap support fitting occurred during a fatigue test. The bushing installation of the flap support fitting is similar to the bushing installation of the actuator fittings of the aileron trim tabs. In the event of failure of the redundant trim tab actuator, such a failure of the bushing could lead to trim tab flutter and consequent structural failure of the trim tab and reduced controllability of the airplane.
Explanation of Relevant Service Information
Saab has issued Service Bulletin 2000-57-011, dated October 1, 1998, which describes procedures for repetitive visual inspections to detect looseness or gap of the press fit bushing installation of the actuation fittings of the aileron trim tabs. In addition, the service bulletin describes procedures for eventual replacement of existing bushings with new, staked bushings in the fittings. Such replacement when accomplished, eliminates the need for the repetitive inspections. The service bulletin also describes procedures for an optional temporary preventive action that involves the installation of washers on the bushings of the actuator fittings of the aileron trim tabs. Accomplishment of the actions specified in the service bulletin is intended to adequately address the identified unsafe condition.
The LFV classified this service bulletin as mandatory and issued Swedish airworthiness directive (SAD) No. 1-132, dated October 8, 1998, in order to assure the continued airworthiness of these airplanes in Sweden.
FAA's Conclusions
This airplane model is manufactured in Sweden and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.19) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the LFV has kept the FAA informed of the situation described above. The FAA has examined the findings of the LFV, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.
Explanation of Requirements of the Rule
Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, this AD is being issued to prevent looseness or gap of the press fit bushing installation of the actuator fittings of the aileron trim tabs. This AD requires accomplishment of the actions specified in the service bulletin described previously, except as discussed below.
Differences Between this AD and Service Bulletin
Operators should note that, although the service bulletin specifies that the manufacturer may be contacted for disposition of a certain repair condition, this AD requires the repair of that condition to be accomplished in accordance with a method approved by the FAA, or the LFV (or its delegated agent).
Cost Impact
None of the airplanes affected by this action are on the U.S. Register. All airplanes included in the applicability of this rule currently are operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, the FAA considers that this rule is necessary to ensure that the unsafe condition is addressed in the event that any of these subject airplanes are imported and placed on the U.S. Register in the future.
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Should an affected airplane be imported and placed on the U.S. Register in the future, it would require approximately 3 work hours to accomplish the required inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspection would be $180 per airplane, per inspection cycle.
It would require approximately 12 work hours for the bushing replacement, at an average labor rate of $60 per work hour. Required parts would be provided by the manufacturer at no cost to the operator. Based on these figures, the cost impact of the installation would be $720 per airplane.
Should an operator elect to accomplish the optional temporary preventive action, it would take approximately 8 work hours to accomplish it, at an average labor rate of $60 per work hour. Required parts would be provided by the manufacturer at no cost to the operator. Based on these figures, the cost impact of the optional temporary preventive action would be $480 per airplane.
Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently on the U.S. register, it has no adverse economic impact and imposes no additional burden on any person. Therefore, prior notice and public procedures hereon are unnecessary and the amendment may be made effective in less than 30 days after publication in the Federal Register.
Comments Invited
Although this action is in the form of a final rule and was not preceded by notice and opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ``ADDRESSES.'' All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.
Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filedin the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this rule must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket Number 98-NM-350-AD.'' The postcard will be date stamped and returned to the commenter.
Regulatory Impact
The regulations adopted herein will not have substantial direct effects 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, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.
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
-
The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
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Section 39.13 is amended by adding the following new airworthiness directive:
99-15-12 Saab Aircraft AB: Amendment 39-11232. Docket 98-NM-350-AD.
Applicability: Model SAAB 2000 series airplanes having serial numbers -004 through -011 inclusive and -013 through -016 inclusive, certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To detect looseness or gap of the press fit bushing installation of the actuation fittings of the aileron trim tabs, which, in the event of failure of the redundant trim tab actuator, could lead to trim tab flutter and consequent structural failure of the trim tab, accomplish the following:
Inspection
(a) Within 400 flight hours after the effective date of this AD, perform a detailed inspection of the bushing installation of the actuator fittings of the aileron trim tabs to detect looseness or gap, in accordance with Saab Service Bulletin 2000-57-011, dated October 1, 1998.
(1) If no looseness or gap is found, repeat the inspection thereafter at intervals not to exceed 800 flight hours until the requirements of paragraph (b) of this AD have been accomplished. Accomplishment of the temporary preventive action specified in paragraph 2.C. of the Accomplishment Instructions of the service bulletin terminates the repetitive inspections until the requirements of paragraph (b) of this AD have been accomplished.
(2) Except as specified in paragraph (c) of this AD, if any looseness or gap is found, prior to further flight, accomplish the corrective actions specified in paragraph 2.G. of the Accomplishment Instructions of the service bulletin. Repeat the inspection thereafter at intervals not to exceed 800 flight hours until the requirements of paragraph (b) of this AD have been accomplished. Accomplishment of the temporary preventive action specified in paragraph 2.C. of the Accomplishment Instructions of the service bulletin terminates the repetitive inspections of paragraph (a) of this AD.
Note 2: For the purposes of this AD, a detailed inspection is defined as: ``An intensive visual examination of a specific structural area, system, installation, or
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assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc. may be used. Surface cleaning and elaborate access procedures may be required.''
Terminating Action
(b) Except as specified in paragraph (c) of this AD, within 6,000 flight hours after the effective date of this AD, replace the existing bushings with new, staked bushings in the actuator fittings of the aileron trim tabs in accordance with Saab Service Bulletin 2000-57-011, dated October 1, 1998. Accomplishment of this replacement terminates the requirements of this AD.
Conditional Corrective Action
(c) If, during the accomplishment of the bushing installation inspection required by paragraph (a)(2) or the bushing replacement required by paragraph (b) of this AD, any radial play is detected between the small diameter flanged bushing and the fitting lug hole, and the radial play is 0.006 inch or less, prior to further flight, repair it in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Luftfartsverket (LFV) (or its delegated agent).
Alternative Methods of Compliance
(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.
Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.
Special Flight Permits
(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
Incorporation by Reference
(f) Except as provided in paragraph (c) of this AD, the actions shall be done in accordance with Saab Service Bulletin 2000-57-011, dated October 1, 1998. 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, Linkoping, 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 4: The subject of this AD is addressed in Swedish airworthiness directive (SAD) 1-132, dated October 8, 1998.
(g) This amendment becomes effective on August 6, 1999.
Issued in Renton, Washington, on July 14, 1999. D.L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-18409Filed7-21-99; 8:45 am]
BILLING CODE 4910-13-P
