Airworthiness directives: EXTRA Flugzeugbau GmbH,
[Federal Register: January 24, 2007 (Volume 72, Number 15)]
[Rules and Regulations]
[Page 3050-3052]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24ja07-8]
[[Page 3050]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA-2006-26134; Directorate Identifier 2006-CE-56-AD; Amendment 39-14898; AD 2007-02-11]
RIN 2120-AA64
Airworthiness Directives; EXTRA Flugzeugproduktions-und Vertriebs-GmbH Models EA-300, EA-300S, EA-300L, and EA-300/200 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new airworthiness directive (AD) to supersede AD 2002-21-11, which applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Model EA-300S airplanes. AD 2002-21-11 currently requires you to inspect, using a fluorescent dye check penetrant method, the upper longeron at the horizontal stabilizer attachment for cracks, repair any cracks found, and modify the horizontal stabilizer. That AD also requires a limit on operation to the Normal category until the initial inspection and modification on airplanes with less than 200 hours time-in-service is done. Since we issued AD 2002-21-11, cracks have been found on Models EA-300L and EA-300/200 airplanes. Consequently, this AD adds airplanes to the Applicability section and requires you to inspect and modify the upper longeron at the horizontal stabilizer attachment. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect, correct, and prevent cracks in the upper longeron at the horizontal stabilizer attachment, which could result in structural failure of the aft fuselage. This failure could lead to loss of control.
DATES: This AD becomes effective on February 28, 2007.
As of February 28, 2007, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation.
ADDRESSES: For service information identified in this AD, contact EXTRA Flugzeugproduktions-und Vertriebs-GmbH, Schwarze Heide 21, D-46569 Huenxe, Germany; fax: (+49)-2858-9137-42.
To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-26134; Directorate
Identifier 2006-CE-56-AD.
FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
On November 15, 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 certain EXTRA Flugzeugproduktions-und Vertriebs-GmbH (EXTRA) Models EA-300, EA-300S, EA-300L, and EA-300/200 airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on November 22, 2006 (71 FR 67499). The NPRM proposed to supersede AD 2002-21-11, Amendment 39-12917 (67 FR 65479, October 25, 2002), with a new AD that would require you to do the following:
Inspect the upper longeron at the horizontal stabilizer attachment for cracks;
Reinforce the upper longeron in the area of the horizontal stabilizer attachment; and
Install V-tubes to reinforce fuselage frame underneath the horizontal stabilizer attachment bracket on Models EA-300S and EA-300L airplanes only.
Comments
We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public.
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:
Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was already proposed in the NPRM.
Differences Between the European Authority AD, the Service Bulletin, and This AD
EASA AD No. 2006-0281, dated September 14, 2006, and EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006, allow 50-hour repetitive inspections of the horizontal stabilizer attachment with the option of installing the modification kits as a terminating action for the repetitive inspections for certain affected airplanes. This AD does not allow continued repetitive inspections.
The FAA has determined that long-term continued operational safety is better assured by design changes that remove the source of the problem rather than by repetitive inspections or other special procedures.
Costs of Compliance
We estimate that this AD affects 134 airplanes in the U.S. registry.
We estimate the following costs to do the inspection:
Labor cost
Parts cost
Total cost per airplane
Total cost on U.S. operators
24 work-hours x $80 per hour = Not applicable................. $1,920................................. $1,920 x 134 = $257,280. $1,920.
We estimate the following costs to do the modifications:
Labor cost
Parts cost
Total cost per airplane
Total cost on U.S. operators
40 work-hours x $80 per hour = $200........................... $3,200 + $200 = $3,400................. $3,400 x 134 = $455,600. $3,200.
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For airplanes still covered under warranty, the manufacturer will provide warranty credit for up to 35 work-hours for the inspection and modification work, as stated on page 8 of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006.
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. FAA-2006-26134; Directorate Identifier 2006-CE-56-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
0 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 39--AIRWORTHINESS DIRECTIVES
0 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]
0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2002-21-11, Amendment 39-12917 (67 FR 65479, October 25, 2002) and adding the following new AD:
2007-02-11 EXTRA Flugzeugproduktions-und Vertriebs-GmbH: Amendment 39-14898; Docket No. FAA-2006-26134; Directorate Identifier 2006-CE- 56-AD.
Effective Date
(a) This AD becomes effective on February 28, 2007.
Affected ADs
(b) This AD supersedes AD 2002-21-11, Amendment 39-12917.
Applicability
(c) This AD applies to the following airplanes that are certificated in any category:
Models
Serial Nos.
EA-300................................. 01 through 62. EA-300L................................ 01 through 71, 73 through 77, 79 through 83, 85 through 89, 91, and 92. EA-300S................................ 01 through 29. EA-300/200............................. 01 through 31 and 1032 through 1039.
Unsafe Condition
(d) This AD is the result from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified in this AD are intended to detect, correct, and prevent cracks in the upper longeron at the horizontal stabilizer attachment, which could result in structural failure of the aft fuselage. This failure could lead to loss of control.
Compliance
(e) To address this problem, you must do the following, unless already done:
Actions
Compliance
Procedures
(1) Inspect, using a
(i) For Models EA-300S Follow Part I of fluorescent dye penetrant airplanes: Upon
EXTRA Service method, the upper longeron at accumulating 250
Bulletin No. the horizontal stabilizer hours time-in-service 300-2-95, attachment for cracks, as (TIS) after December Issue: F, applicable. You may take
17, 2002 (the
Dated: July 10, ``unless already done''
effective date of AD 2006. credit for the inspections if 2002-21-11) or within you previously used Extra the next 50 hours TIS Service Bulletin No. 300-2-95 after February 28, (pages 2-6 at Issue: C, dated 2007 (the effective July 15, 1998; and pages 1 date of this AD), and 7 through 11 at Issue: D, whichever occurs dated January 30, 2001).
first. (ii) For Models EA-300, EA- 300L, and EA-300/200 airplanes: Within the next 50 hours TIS after February 28, 2007 (the effective date of this AD). (iii) For all affected airplanes: If the modifications specified in Part II and Part III of EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006, have already been incorporated, no further action is required.
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(2) If cracks are found during For all affected
Follow Part II the inspection required in airplanes: Before of EXTRA paragraph (e)(1) of this AD further flight after Service in areas A, B, and C (as
the inspection
Bulletin No. shown in Figure 1 of EXTRA required in paragraph 300-2-95, Service Bulletin No. 300-2- (e)(1) of this AD in Issue: F, 95, Issue: F, Dated: July 10, which cracks are
Dated: July 10, 2006), weld the crack and found, unless already 2006. modify the upper longeron at done. the horizontal stabilizer attachment by installing the applicable modification kit (or FAA-approved equivalent parts). (3) If no cracks are found For all affected
Follow Part II during the inspection
airplanes: Within the of EXTRA required in paragraph (e)(1) next 100 hours TIS Service of this AD, modify the upper after February 28, Bulletin No. longeron at the horizontal 2007 (the effective 300-2-95, stabilizer attachment by
date of this AD), Issue: F, installing the applicable unless already done. Dated: July 10, modification kit (or FAA-
2006. approved equivalent parts). (4) For Models EA-300S and EA- (i) For Model EA-300S: Follow Part III 300L airplanes only:
Within the next 200 of EXTRA Reinforce the fuselage frame hours TIS after
Service underneath the horizontal December 17, 2002 Bulletin No. stabilizer main spar
(the effective date 300-2-95, attachment bracket by
of AD 2002-21-11) or Issue: F, installing the applicable within the next 100 Dated: July 10, modification kit (or FAA- hours TIS after
2006. approved equivalent parts). February 28, 2007 (the effective date of this AD), whichever occurs first, unless already done. (ii) For Model EA-300L: Within the next 100 hours TIS after February 28, 2007 (the effective date of this AD), unless already done.
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Standards Office, Small Airplane Directorate, FAA, ATTN: Karl Schletzbaum, Aerospace Engineer, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 2002-21-11 are approved for this AD.
Related Information
(h) The European Aviation Safety Agency (EASA) AD No. 2006-0281, dated September 14, 2006, also addresses the subject of this AD.
Material Incorporated by Reference
(i) You must use EXTRA Service Bulletin No. 300-2-95, Issue: F, Dated: July 10, 2006 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 EXTRA Flugzeugproduktions- und Vertriebs- GmbH, Schwarze Heide 21, D-46569 Huenxe, Germany; fax: (+49)-2858-9137-42.
(3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202- 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .
Issued in Kansas City, Missouri on January 12, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-775 Filed 1-23-07; 8:45 am]
BILLING CODE 4910-13-P
