Daily Rules, Proposed Rules, and Notices of the Federal Government
For service information identified in this proposed AD, contact Saab AB, Saab Aeronautics, SE-581 88, Linkoping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; email
You may examine the AD docket on the Internet at
We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the
We will post all comments we receive, without change, to
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012-0068, dated April 25, 2012 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:
On two SAAB 2000 aeroplanes, signs of chafing have been found on the bottom panel of the centre cabin between fuselage station (STA) 562 and STA 622. The investigation results have shown that the chafing is caused by certain Hi Lok fasteners, installed as a repair during production, through the upper wing skin panel.
This condition, if not detected and corrected, could affect the structural integrity of the affected wing-to-fuselage connection.
To address this potential unsafe condition, SAAB issued Service Bulletin (SB) 2000-53-057 to provide instructions for a general visual inspection to detect chafing in the area between the upper wing skin and the cabin centre bottom panel and to verify if there are Hi Lok fasteners installed with the collar up.
For the reasons described above, this [EASA] AD requires a one-time inspection of the designated area, the accomplishment of corrective action(s) [repair], depending on findings, and the reporting of all inspection results * * *.
This [EASA] AD is considered an interim action and further AD action may follow.
Saab AB, Saab Aerosystems has issued Service Bulletin 2000-53-057, dated November 22, 2011. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.
Saab Service Bulletin 2000-53-057, dated November 22, 2011, specifies to contact the manufacturer for repair instructions, but this proposed AD would require doing the repair using a method that we approve.
Based on the service information, we estimate that this proposed AD would affect about 10 products of U.S. registry. We also estimate that it would take about 4 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $3,400, or $340 per product.
We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this proposed AD.
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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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.
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);
3. Will not affect intrastate aviation in Alaska; and
4. 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 proposed AD and placed it in the AD docket.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
1. The authority citation for part 39 continues to read as follows:
49 U.S.C. 106(g), 40113, 44701.
2. The FAA amends § 39.13 by adding the following new AD:
We must receive comments by November 16, 2012.
This AD applies to Saab AB, Saab Aerosystems Model SAAB 2000 airplanes, certificated in any category, all serial numbers.
Air Transport Association (ATA) of America Code 53, Fuselage.
This AD was prompted by reports of chafing on the bottom panel of the center cabin. We are issuing this AD to detect and correct any chafing on the bottom panel of the center cabin, which could affect the structural integrity of the affected wing-to-fuselage connection.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 12 months after the effective date of this AD, do a general visual inspection of the area between the upper part of the wing skin and the center bottom panel to determine if any Hi Lok fasteners are installed with the collar up, and do all applicable related investigative actions, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000-53-057, dated November 22, 2011.
If any chafing or damage is found during any inspection required by paragraph (g) of this AD: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD to Saab AB, Saab Aerosystems, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000-53-057, dated November 22, 2011, at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. The report must include the inspection results, the airplane serial number, and the number of landings and flight hours on the airplane.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
The following provisions also apply to this AD:
(1) Refer to MCAI EASA Airworthiness Directive 2012-0068, dated April 25, 2012;
(2) For service information identified in this AD, contact Saab AB, Saab Aeronautics, SE-581 88, Linköping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; email