[Federal Register Volume 62, Number 14 (Wednesday, January 22, 1997)] [Rules and Regulations] [Pages 3209-3211] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 97-1439] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. 95-NM-201-AD; Amendment 39-9891; AD 96-25-06 R1] RIN 2120-AA64 Airworthiness Directives; Saab Model SAAB SF340A and SAAB 340B Series Airplanes AGENCY: Federal Aviation Administration, DOT. [[Page 3210]] ACTION: Final rule; correction. ----------------------------------------------------------------------- SUMMARY: This document corrects information in an existing airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that currently requires inspections to detect damage or cracking of the forward and aft attachment lugs of the flap fittings at wing station (WS) 123.38; an inspection to verify that the sizes of the holes of the flap fittings are within specified limits and to ensure that the swaged bushings are not loose; and modification of the flap fittings. This action corrects information concerning the terminating action for the requirements of the AD. This action is necessary to ensure that operators are not required to perform additional actions unnecessarily after modifying their airplanes. DATES: Effective January 27, 1997. The incorporation by reference of certain publications listed in the regulations was previously approved by the Director of the Federal Register as of January 27, 1997 (61 FR 66885, December 19, 1996). FOR FURTHER INFORMATION CONTACT: Ruth Harder, Aerospace Engineer, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 227-1721; fax (206) 227-1149. SUPPLEMENTARY INFORMATION: On December 2, 1996, the FAA issued AD96-25- 06, amendment 39-9848 (61 FR 66885, December 19, 1996). That AD requires repetitive inspections to detect damage or cracking of the forward and aft attachment lugs of the flap fittings at wing station (WS) 123.38; an inspection to verify that the sizes of the holes of the flap fittings are within specified limits and to ensure that the swaged bushings are not loose; and modification of the flap fittings. That AD action was prompted by a report of jamming of a flap due to incorrect tolerances of the flap-hinge installation, which caused high bearing stress on the bushings in the flap fittings. The actions required by that AD are intended to prevent such high bearing stress, which could result in wear on the bushings, cracking of the flap fittings, and breakage of the lugs; these conditions could result in jamming of the flaps and consequent reduced controllability of the airplane. Explanation of Necessary Correction of AD Recently, the FAA has become aware of the fact that, as AD 96-25-06 is currently worded, certain of the terminating action provisions in it are not clear. Specifically, paragraph (a) of the AD requires repetitive visual inspections to detect cracking of the forward and aft attachment lugs of the flap fittings at wing station (WS) 123.38. Paragraph (a)(2) of the AD states that, if any cracking is found during one of these visual inspections, operators must immediately replace the flap fittings with new improved flap fittings and install improved bushings. This installation is specified as Modification 2628--Part 3 in the Accomplishment Instructions of Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. Paragraph (a)(2) of the AD then states, ``After this modification is accomplished, no further action is required by this paragraph.'' While it is correct that the operators who accomplished that modification would not have to continue to perform the visual inspections required by paragraph (a), they also would not have to accomplish any other portion of the AD. In other words, that modification constitutes terminating action for the requirements of the AD, not merely the requirements of paragraph (a). While AD 96-25-06 may have been unclear on this point, it was the FAA's intent that the modification be considered terminating action for the requirements of the AD. Additionally, the referenced Saab service bulletin (340-57-027), as well as the parallel Swedish airworthiness directive (SAD No. 1-072), indicate that no further work is required of operators who accomplish Modification 2628--Part 3. Corrective Action Taken The FAA has determined that it is appropriate to take action to correct paragraph (a)(2) of AD 96-25-06 to state: ``After this modification is accomplished, no further action is required by this AD.'' The FAA finds this correction is necessary in order to prevent operators from having to perform additional and unnecessary work on these airplanes. Action is taken herein to correct the error and to correctly add the AD as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13). The effective date of the AD remains January 27, 1997. The AD is being reprinted in its entirety, below, for the convenience of affected operators. No Need for Additional Notice and Public Comment Since this action only clarifies the intent of a provision of an AD, and relieves affected operators from having to perform what could be additional and unnecessary work, it has no adverse economic impact and imposes no additional burden on any person. Therefore, notice and public procedures hereon are unnecessary. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Correction 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. Sec. 39.13 [Amended] 2. Section 39.13 is amended by removing amendment 39-9848 (61 FR 66885, December 19, 1996), and by adding a new airworthiness directive (AD), amendment 39-9891, to read as follows: 96-25-06 R1 SAAB Aircraft AB: Amendment 39-9891. Docket 95-NM-201- AD. Revises AD 96-25-06, amendment 39-9848. Applicability: Model SAAB SF340A series airplanes, serial numbers 004 through 159 inclusive; and Model SAAB 340B series airplanes, serial numbers 160 through 379 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 otherwise 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 (c) 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 high bearing stress on the bushings in the flap fittings, which could result in jamming of the flaps and consequent reduced controllability of the airplane, accomplish the following: (a) Within 800 hours time-in-service after the effective date of this AD: Perform a visual inspection to detect damage or cracking of the forward and aft attachment lugs of the [[Page 3211]] flap fittings at wing station (WS) 123.38, in accordance with Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. (1) If no cracking or damage is found, and the flap fittings have not been modified or replaced, repeat the visual inspection thereafter at intervals not to exceed 800 hours time-in-service. (2) If any cracking is found, prior to further flight, replace the flap fittings with new improved flap fittings, and install improved bushings, in accordance with the Accomplishment Instructions (Modification 2628--Part 3) of the service bulletin. After this modification is accomplished, no further action is required by this AD. (b) Within 4,500 hours time-in-service after the effective date of this AD, perform an inspection to determine the size of the inboard and outboard holes (swaged bushings) of the flap fittings, and to detect loose swaged bushings, in accordance with Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. (1) If the sizes of the holes are within the limits specified in the service bulletin, and if no loose swaged bushings are found, prior to further flight, install improved bushings in accordance with the Accomplishment Instructions (Modification 2628--Part 1) of the service bulletin. After this modification is accomplished, no further action is required by this AD. (2) If the size of any hole is outside the limits specified in the service bulletin, or if any loose swaged bushing is found, prior to further flight, install oversize bushings in the flap fittings, and install improved bushings, in accordance with the Accomplishment Instructions (Modification 2628--Part 2) of the service bulletin. After this modification is accomplished, no further action is required by this AD. (c) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) 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. (e) The inspections, replacement, and installations shall be done in accordance with Saab Service Bulletin SAAB 340-57-027, Revision 01, dated June 30, 1995. 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, as of January 27, 1997 (61 FR 66885, December 19, 1996). 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. (f) This amendment is effective January 27, 1997. Issued in Renton, Washington, on January 14, 1997. S. R. Miller, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 97-1439 Filed 1-21-97; 8:45 am] BILLING CODE 4910-13-U