Airworthiness directives: Saab,
[Federal Register: September 15, 1999 (Volume 64, Number 178)]
[Rules and Regulations]
[Page 49964-49966]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15se99-3]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-220-AD; Amendment 39-11310; AD 99-19-21]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB SF340A and SAAB 340B 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 SF340A and SAAB 340B series airplanes, that requires repetitive inspections to detect cracking around certain fastener holes and adjacent areas of the front spar of the horizontal stabilizers; and corrective actions, if necessary. This amendment also requires repetitive x-ray inspections, cold working of certain fastener holes of the front spar of the horizontal stabilizers, and follow-on actions; and installation of new fasteners, which constitutes terminating action for the repetitive inspections required by this AD. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the front spar due to fatigue cracking around certain fastener holes of the front spar of the horizontal stabilizers, which could result in reduced structural integrity of the airplane.
DATES: Effective October 20, 1999.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of October 20, 1999. ADDRESSES: 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 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: 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: 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 SF340A and SAAB 340B series airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on July 15, 1999 (64 FR 38150). That action proposed to require repetitive inspections to detect cracking around certain fastener holes and adjacent areas of the front spar of the horizontal stabilizers; and corrective actions, if necessary. That action also proposed to require cold working of certain fastener holes of the front spar of the horizontal stabilizers, and follow-on actions; and installation of new fasteners, which would constitute terminating action for the repetitive inspections. That action also proposed to add repetitive x-ray inspections.
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.
Explanation of Change Made to Final Rule
The FAA has added a note to the final rule to clarify the definition of a detailed visual inspection.
Conclusion
After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the change described previously. The FAA has determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.
Cost Impact
The FAA estimates that 279 airplanes of U.S. registry will be affected by this AD.
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It will take approximately 4 work hours per airplane to perform the required detailed visual inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspection required by this AD on U.S. operators is estimated to be $66,960, or $240 per airplane, per inspection cycle.
It will take approximately 6 work hours per airplane to accomplish the required eddy current and x-ray inspections, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspections required by this AD on U.S. operators is estimated to be $100,440, or $360 per airplane, per inspection cycle.
It will take approximately 42 work hours to accomplish the cold working of the fastener holes, at an average labor rate of $60 per work hour. Required parts will cost approximately $400 per airplane. Based on these figures, the cost impact of the cold work required by this AD on U.S. operators is estimated to be $814,680, or $2,920 per airplane.
The cost impact figures discussed above are 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.
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: 99-19-21 SAAB Aircraft AB: Amendment 39-11310. Docket 98-NM-220- AD.
Applicability: Model SAAB SF340A series airplanes, manufacturer's serial numbers -004 through -159 inclusive; and SAAB 340B series airplanes, manufacturer's serial numbers -160 through - 439 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 (f) 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 prevent failure of the front spar due to fatigue cracking around certain fastener holes of the front spar of the horizontal stabilizers, which could result in reduced structural integrity of the airplane, accomplish the following:
Note 2: For the purposes of this AD, a detailed visual inspection is defined as: ``An intensive visual examination of a specific structural area, system, installation, or 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.''
Initial and Repetitive Inspections
(a) For Model SAAB SF340A series airplanes with manufacturer's serial numbers -004 through -159 inclusive: Perform the inspections (detailed visual, eddy current, and x-ray) specified in paragraph 2.D. of the Accomplishment Instructions of Saab Service Bulletin 340-55-033, Revision 04, dated December 1, 1998, to detect cracking around certain fastener holes and adjacent areas of the front spar of the horizontal stabilizer, in accordance with the service bulletin, at the time specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable. Thereafter, repeat only the eddy current and x-ray inspections at intervals not to exceed 12,000 flight cycles until the requirements of paragraph (d) of this AD are accomplished.
(1) For airplanes that have accumulated less than 22,000 total flight cycles as of the effective date of this AD: Perform an eddy current and an x-ray inspection prior to the accumulation of 22,000 total flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later.
(2) For airplanes that have accumulated 22,000 or more total flight cycles and less than 30,000 total flight cycles as of the effective date of this AD: Accomplish the requirements of paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.
(i) Perform a detailed visual inspection within 800 flight cycles after the effective date of this AD; and
(ii) Perform an eddy current and an x-ray inspection within 2,000 flight cycles after the effective date of this AD.
(3) For airplanes that have accumulated 30,000 or more total flight cycles as of the effective date of this AD: Accomplish the requirements of paragraphs (a)(3)(i) and (a)(3)(ii) of this AD.
(i) Perform a detailed visual inspection within 400 flight cycles after the effective date of this AD; and
(ii) Perform an eddy current and an x-ray inspection within 1,200 flight cycles after the effective date of this AD.
Initial and Repetitive Inspections
(b) For Model SAAB 340B series airplanes with manufacturer's serial numbers -160 through -439 inclusive: Perform the inspections (detailed visual, eddy current, and x-ray) specified in paragraph 2.D. of the Accomplishment Instructions of Saab Service Bulletin 340-55-033, Revision 04, dated December 1, 1998, to detect cracking around certain fastener holes and adjacent areas of the front spar of the horizontal stabilizer, in accordance with the service bulletin, at the time specified in paragraph (b)(1), (b)(2), or (b)(3) of this AD, as applicable. Thereafter, repeat only the eddy current and x-ray inspections at intervals not to exceed 6,000 flight cycles until the requirements of paragraph (d) of this AD are accomplished.
(1) For airplanes that have accumulated less than 12,000 total flight cycles as of the effective date of this AD: Perform an eddy current and an x-ray inspection prior to the accumulation of 12,000 total flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later.
(2) For airplanes that have accumulated 12,000 or more total flight cycles and less than 16,000 total flight cycles as of the effective date of this AD: Accomplish the requirements of paragraphs (b)(2)(i) and (b)(2)(ii) of this AD.
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(i) Perform a detailed visual inspection within 800 flight cycles after the effective date of this AD; and
(ii) Perform an eddy current and an x-ray inspection within 2,000 flight cycles after the effective date of this AD.
(3) For airplanes that have accumulated 16,000 or more total flight cycles as of the effective date of this AD: Accomplish the requirements of paragraphs (b)(3)(i) and (b)(3)(ii) of this AD.
(i) Perform a detailed visual inspection within 400 flight cycles after the effective date of this AD; and
(i) Perform a detailed visual inspection within 400 flight cycles after the effective date of this AD; and (ii) Perform an eddy current and an x-ray inspection within 1,200 flight cycles after the effective date of this AD.
Corrective Actions
(c) If any cracking is detected during any inspection required by paragraph (a) or (b) of this AD, prior to further flight, either repair 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); or accomplish the requirements of paragraph (d) of this AD.
Note 3: Inspections to detect cracking around certain fastener holes and adjacent areas of the front spar of the horizontal stabilizers that have been accomplished prior to the effective date of this AD in accordance with Saab Service Bulletin 340-55-033, Revision 03, dated January 22, 1998, are considered acceptable for compliance with the applicable action specified by this AD.
Terminating Action
(d) For all airplanes: Except as provided by paragraph (e) of this AD, accomplish cold working of certain fastener holes of the front spar of the horizontal stabilizers, and follow-on actions; and install new fasteners; in accordance with Saab Service Bulletin 340- 55-034, dated October 16, 1998; at the time specified in paragraph (d)(1), (d)(2), or (d)(3) of this AD, as applicable. Accomplishment of this action constitutes terminating action for this AD.
(1) For all airplanes that have accumulated less than 26,000 total flight cycles as of the effective date of this AD: Within 10,000 flight cycles after the effective date of this AD.
(2) For all airplanes that have accumulated 26,000 or more total flight cycles and less than 30,000 total flight cycles as of the effective date of this AD: Within 6,000 flight cycles after the effective date of this AD.
(3) For all airplanes that have accumulated 30,000 or more total flight cycles as of the effective date of this AD: Within 3,000 flight cycles after the effective date of this AD.
(e) If any crack is detected during the accomplishment of paragraph (d) of this AD, and if the service bulletin listed in paragraph (d) of this AD specifies to contact the manufacturer for an appropriate corrective action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, or the LFV (or its delegated agent).
Alternative Method of Compliance
(f) 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 4: 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
(g) 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
(h) Except as provided by paragraphs (c) and (e) of this AD, the actions shall be done in accordance with Saab Service Bulletin 340- 55-033, Revision 04, dated December 1, 1998; and Saab Service Bulletin 340-55-034, dated October 16, 1998; as applicable. 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 5: The subject of this AD is addressed in Swedish airworthiness directives 1-110R2, dated December 7, 1998, and 1-133, dated October 20, 1998.
(i) This amendment becomes effective on October 20, 1999.
Issued in Renton, Washington, on September 1, 1999. Dorenda D. Baker, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-23352Filed9-14-99; 8:45 am]
BILLING CODE 4910-13-P
