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Docket ID: [Docket No. FAA-2007-29331; Directorate Identifier 2007-NM-136-AD; Amendment 39-15459; AD 2008-08-07]
RIN ID: RIN 2120-AA64
SUBJECT CATEGORY: Airworthiness Directives; Saab Model SAAB-Fairchild SF340A (SAAB/ SF340A) and SAAB 340B Airplanes
The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 19, 2008.
DOCUMENT SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
A crack has been found in an axle adaptor during fatigue testing. It was found that the internal edges of the dowel holes did not have the correct radius and the crack had developed from the edge of one of the dowel holes.
A crack in the axle adaptor can cause the axle adaptor to fail and ultimately lead to loss of [the] wheels and total loss of brake capability.
We are issuing this AD to require actions to correct the unsafe condition on these products.
SUMMARY: Saab Model SAAB Fairchild SF340A (SAAB/SF340A) and SAAB 340B Airplanes,
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR [[Page 19984]]
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on September 28, 2007
(72 FR 55116). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:
A crack has been found in an axle adaptor during fatigue testing. It was found that the internal edges of the dowel holes did not have the correct radius and the crack had developed from the edge of one of the dowel holes.
A crack in the axle adaptor can cause the axle adaptor to fail and ultimately lead to loss of [the] wheels and total loss of brake capability.
The corrective action includes doing repetitive ultrasonic inspections to detect cracking in the axle adaptor; replacing the axle adaptor if necessary; and ultimately doing the terminating action of inspecting and modifying the main landing gear (MLG) shock strut and axle adaptors. The inspection is a crack test. The modification includes measuring the dowel hole, and corrective actions if necessary (replacing the axle adaptor, repairing the dowel hole) and, when accomplished, terminates the repetitive inspection requirements. You may obtain further information by examining the MCAI in the AD docket. Comments
We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public.
We have revised paragraph (f)(5) of the final rule to clarify the applicable service bulletin revisions for the parts installation. Conclusion
We reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. We determined that this change will not increase the economic burden on any operator or increase the scope of the AD. Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.
We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD.
We estimate that this AD will affect about 220 products of U.S. registry. We also estimate that it will take about 9 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per workhour. Required parts cost would be negligible. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $158,400, or $720 per product.
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.
We 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 this AD:
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.
You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 6475527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39AIRWORTHINESS 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. The FAA amends Sec. 39.13 by adding the following new AD:
20080807 Saab Aircraft AB: Amendment 3915459. Docket No. FAA 200729331; Directorate Identifier 2007NM136AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 19, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes listed in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category, unless equipped
with main landing gear (MLG) shock struts modified in accordance with APPH Service Bulletin AIR830643212 or AIR830223232.
(1) Saab Model SAABFairchild SF340A (SAAB/SF340A) airplanes, serial numbers (S/Ns) SF340A004 through 159.
(2) Saab Model SAAB 340B airplanes, S/Ns 340B160 through 459. [[Page 19985]]
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing Gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:
A crack has been found in an axle adaptor during fatigue testing. It was found that the internal edges of the dowel holes did not have the correct radius and the crack had developed from the edge of one of the dowel holes.
A crack in the axle adaptor can cause the axle adaptor to fail and ultimately lead to loss of [the] wheels and total loss of brake capability.
The corrective action includes doing repetitive ultrasonic
inspections to detect cracking in the axle adaptor; replacing the
axle adaptor if necessary; and ultimately doing the terminating
action of inspecting and modifying the main landing gear (MLG) shock
strut and axle adaptors. The inspection is a crack test. The
modification includes measuring the dowel hole and corrective
actions if necessary (replacing the axle adaptor, repairing the
dowel hole), and, when accomplished, terminates the repetitive inspection requirements.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 8,000 flight cycles since the last MLG overhaul, or
within 1,500 flight cycles, or 6 months after the effective date of
this AD, whichever occurs latest: Inspect the MLG in accordance with
the Accomplishment Instructions of Saab Service Bulletin 34032133,
Revision 01, dated May 3, 2006. If any crack is found, before
further flight: Replace the axle adaptor in accordance with the
Accomplishment Instructions of Saab Service Bulletin 34032133, Revision 01, dated May 3, 2006.
(2) Repeat the inspection required by paragraph (f)(1) of this
AD thereafter at intervals not to exceed 2,000 flight cycles until
the terminating action required by paragraph (f)(3) of this AD is accomplished.
(3) Within 12,000 flight cycles after the effective date of this
AD, or at the next MLG overhaul, whichever occurs earlier: Inspect
and modify the MLG shock strut and axle adaptors in accordance with
the Accomplishment Instructions of APPH Service Bulletin AIR83064
3212, Revision 3, dated April 26, 2006; or AIR830223232, Revision 3, dated April 26, 2006; as applicable.
(4) Actions done before the effective date of this AD in
accordance with the service bulletins listed in paragraphs
(f)(4)(i), (f)(4)(ii), and (f)(4)(iii) of this AD, as applicable,
are acceptable for compliance with the corresponding actions in this AD.
(i) Saab Service Bulletin 34032133, dated April 19, 2006.
(ii) APPH Service Bulletin AIR830643212, dated January 2006;
Revision 1, dated January 23, 2006; and Revision 2, dated March 30, 2006.
(iii) APPH Service Bulletin AIR830223232, dated January 2006;
Revision 1, dated January 23, 2006; and Revision 2, dated March 30, 2006.
(5) As of the effective date of this AD, no person may install
an MLG shock strut having part number (P/N) AIR83022 or AIR83064, or
axle adaptor having P/N AIR127308, AIR390226, or AIR130238, unless
it has been inspected and modified in accordance with APPH Service
Bulletin AIR830223232 or AIR830643212, as specified in paragraph
(f)(3), (f)(4)(ii), or (f)(4)(iii) of this AD, as applicable. FAA AD Differences
Note: This AD differs from the MCAI and/or service information as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM
116, International Branch, Transport Airplane Directorate, FAA, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Mike
Borfitz, Aerospace Engineer, International Branch, ANM116, FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington 980573356; telephone (425) 2272677; fax (425) 2271149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAAapproved. Corrective actions are considered
FAAapproved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120 0056.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 20060263, dated
August 29, 2006; Saab Service Bulletin 34032133, Revision 01,
dated May 3, 2006; APPH Service Bulletin AIR830643212, Revision 3,
dated April 26, 2006; and APPH Service Bulletin AIR830223232, Revision 3, dated April 26, 2006; for related information.
Material Incorporated by Reference
(i) You must use the service information specified in Table 1 of
this AD to do the actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact Saab Aircraft AB, SAAB Aircraft Product Support, S581.88,
Link[ouml]ping, Sweden.
(3) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 7416030,
or go to: http://www.archives.gov/federalregister/cfr/ibr locations.html.
Table 1.Material Incorporated by Reference
Service Bulletin Revision Date
APPH Service Bulletin 3 April 26, 2006. AIR830223232.
APPH Service Bulletin 3 April 26, 2006. AIR830643212.
Saab Service Bulletin 34032 01 May 3, 2006.
133.
Issued in Renton, Washington, on March 31, 2008. Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E87299 Filed 41108; 8:45 am]
BILLING CODE 491013P
FOR FURTHER INFORMATION CONTACT Mike Borfitz, Aerospace Engineer, International Branch, ANM116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 980573356; telephone (425) 2272677; fax (425) 2271149.
14 CFR Part 39 40 CFR Part 52 14 CFR Part 71 33 CFR Part 165 50 CFR Part 679 47 CFR Part 73 26 CFR Part 1 40 CFR Part 180 33 CFR Part 117 50 CFR Part 17 44 CFR Part 67 50 CFR Part 648 14 CFR Part 97 33 CFR Part 100 40 CFR Part 63 50 CFR Part 622 44 CFR Part 65 50 CFR Part 660 26 CFR Part 301 39 CFR Part 111 40 CFR Part 300 6 CFR Part 5 40 CFR Part 271 47 CFR Part 64 40 CFR Parts 52 and 81 50 CFR Part 665 44 CFR Part 64 10 CFR Part 50 49 CFR Part 571 47 CFR Part 76