Federal Register: October 27, 2006 (Volume 71, Number 208)
DOCID: FR Doc E6-17828
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
CFR Citation: 14 CFR Part 39
Docket ID: [Docket No. FAA-2006-24228; Directorate Identifier 2006-CE-22-AD; Amendment 39-14805; AD 2006-22-08]
RIN ID: RIN 2120-AA64
ACTION: Airworthiness directives:
DOCUMENT ACTION: Final rule.
Airworthiness Directives; Air Tractor, Inc. Models AT-602, AT- 802, and AT-802A Airplanes
DATES: This AD becomes effective on December 1, 2006.
As of December 1, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation.
The FAA adopts a new airworthiness directive (AD) for all Air Tractor, Inc. Models AT602, AT802, and AT802A airplanes. This AD requires you to repetitively inspect the engine mount for any cracks, repair or replace any cracked engine mount, and report any cracks found to the FAA. This AD results from reports of cracked engine mounts. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane.
Air Tractor, Inc.,
On April 26, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Air Tractor, Inc. Models AT602, AT802, and AT802A airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on May 2, 2006 (71 FR 25793). The NPRM proposed to require you to repetitively inspect the engine mount for any cracks, repair or replace any cracked engine mount, and report any cracks found to the FAA.
We provided the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and FAA's response to the comment:
Comment Issue: Flight Test and Analysis
Ronald G. Bush suggests that proper flight testing of a correctly instrumented engine mount and structure, combined with analysis of the data collected, may provide for a more efficient solution to the cracking problem than the repetitive inspections currently provide. He notes that the cost of each inspection is estimated at $120, and a properly substantiated terminating action may prove less costly over time.
We partially agree that a properly executed flight test and analysis is a method to provide substantiating data that can be used to validate an alternate method for addressing the engine mount fatigue cracking. The FAA has not received any data at this time that proposes and substantiates a terminating action for the required inspections. If and when such information is received, we will consider mandating it through AD action.
We are not changing the AD as a result of this comment. Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these minor corrections:
Costs of Compliance
We estimate that this AD affects 368 airplanes in the U.S. registry.
We estimate the following costs to do each required inspection: Total cost per Total cost on U.S. Labor cost Parts cost airplane per operators for initial inspection inspection 1.5 workhours x $80 per hour = $120... Not Applicable............ $120 368 x $120 = $44,160.
We have no way of determining the number of airplanes that may need
replacement of the engine mount. We estimate the following costs to do the replacement:
Total cost per Labor cost Parts cost airplane per Total cost on U.S. operators inspection for initial inspection 81 workhours x $80 per hour = $6,480........ $3,982 $10,462 368 x $10,462 = $3,850,016. [[Page 62911]]
Any required ``uponcondition'' repairs would vary depending upon the damage found during each inspection. Based on this, we have no way of determining the potential repair costs for each airplane. Authority for This Rulemaking
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 AD. Regulatory Findings
We have 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 that 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 summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ``Docket No. FAA200624228; Directorate Identifier 2006CE22AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under 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 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. FAA amends Sec. 39.13 by adding a new AD to read as follows: 20062208 Air Tractor, Inc.: Amendment 3914805; Docket No. FAA 200624228; Directorate Identifier 2006CE22AD.
(a) This AD becomes effective on December 1, 2006.
(c) This AD affects all Models AT602, AT802, and AT802A airplanes, all serial numbers, that are certificated in any category.
(d) This AD results from reports of cracked engine mounts. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane. Compliance
(e) To address this problem, you must do the following: Actions Compliance Procedures (1) Visually inspect the Initially inspect Follow Snow engine mount for any cracks. upon accumulating Engineering Co. 4,000 hours timein Service Letter service (TIS) or
December 1, 2006
(the effective date
of this AD),
inspect every 300
(2) If you find any crack Before further For obtaining a damage, do one of the flight after any repair scheme: following: inspection required Follow Snow (i) Obtain an FAAapproved by paragraph (e)(1) Engineering Co. repair scheme and of this AD where Service Letter incorporate this repair crack damage is
If you replace the
engine mount, then
4,000 hours TIS and
intervals not to
exceed 300 hours
(3) Report any cracks that Within the next 10 The Office of you find to the FAA at the days after you find Management and address specified in the cracks or Budget (OMB) paragraph (f) of this AD. within the next 10 approved the Include in your report: days after December information (i) Airplane serial number; 1, 2006 (the collection (ii) Airplane and engine effective date of requirements mount hours TIS; this AD), whichever contained in this (iii) Crack location(s) and occurs later. regulation under size(s); the provisions of (iv) Corrective action the Paperwork taken; and Reduction Act and (v) Point of contact name assigned OMB and telephone number. Control Number 2120 0056.
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Fort Worth Airplane Certification Office, FAA, Attn: Andrew McAnaul, Aerospace Engineer, ASW150 (c/o MIDO43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 3083365; facsimile: (210) 3083370, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(g) You must do the actions required by this AD following the instructions in Snow Engineering Co. Service Letter
go to the Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL 401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA200624228; Directorate
Issued in Kansas City, Missouri, on October 13, 2006. James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E617828 Filed 102606; 8:45 am]
BILLING CODE 491013P
FOR FURTHER INFORMATION CONTACT
Andrew McAnaul, Aerospace Engineer, ASW150 (c/o MIDO43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 3083365; facsimile: (210) 3083370.