Airworthiness directives: Tiger Aircraft LLC,
[Federal Register: August 22, 2005 (Volume 70, Number 161)]
[Rules and Regulations]
[Page 48857-48859]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22au05-10]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA-2005-20968; Directorate Identifier 94-CE-15-AD; Amendment 39-14222; AD 95-19-15 R1]
RIN 2120-AA64
Airworthiness Directives; Tiger Aircraft LLC Models AA-5, AA-5A, AA-5B, and AG-5B Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: The FAA is revising Airworthiness Directive (AD) 95-19-15 for all Tiger Aircraft LLC (Type Certificate A16EA formerly held by American General Aircraft Corporation and Grumman American Aviation Corporation) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes. AD 95-19- 15 currently requires you to inspect the wing attach shoulder bolts for fretting, scoring, wear, or enlarged or elongated mounting holes (known as damage from hereon); replace any damaged parts; repair any damaged areas; inspect the wing spar at the center spar clearance gap for excessive clearance; and shim the spar if excessive clearance is found. That AD was written to apply to all serial numbers of all models. A design change was made in this area beginning with serial number 10175 of the Model AG-5B airplanes. Therefore, the action should not apply to Model AG-5B airplanes with a serial number of 10175 or higher. This AD retains all the actions of AD 95-19-15 for all airplanes originally affected, but cuts off the applicability for the Model AG-5B airplanes at serial number 10174. We are issuing this AD to continue to prevent wing attach shoulder bolt failure, which, if not detected and corrected, could lead to structural damage of the wing/fuselage to the point of failure.
DATES: This AD becomes effective on October 3, 2005.
As of October 3, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation.
ADDRESSES: To get the service information identified in this AD, contact Tiger Aircraft LLC, 226 Pilot Way, Martinsburg, WV 25401.
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-2005-20968; Directorate
Identifier 94-CE-15-AD.
FOR FURTHER INFORMATION CONTACT: Richard Beckwith, Aerospace Engineer, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-794-5531; facsimile: 516- 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The FAA has received four reports (three in England and one in the United States) of wing attach shoulder bolt failure on Tiger Aircraft LLC (Type Certificate A16EA formerly held by American General Aircraft Corporation (AGAC) and Grumman American Aviation Corporation (GAAC)) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes. Investigation reveals that excessive wing to center spar clearance could have contributed to the bolt failures; however, in each of the four instances, the bolts failed before reaching the service life of 7,250 hours time-in-service (TIS). The FAA has determined that, to assure the safety of these airplanes, the established service life of these bolts needed review. Our review of service life on Tiger Aircraft LLC (Type Certificate A16EA formerly held by AGAC and GAAC) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes caused us to issue AD 95-19-15, Amendment 39-9377 (60 FR 48628, September 20, 1995). AD 95-19-15 currently requires the following on Tiger Aircraft LLC (Type Certificate A16EA formerly held by AGAC and GAAC) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes, all serial numbers:
--Inspect the wing attach shoulder bolts for fretting, scoring, wear, or enlarged or elongated mounting holes (known as damage from hereon), and replace any damaged parts and repairing any damaged areas; --Inspect the wing spar at the center spar clearance gap for excessive clearance; and --Shim the spar if excessive clearance is found.
AD 95-19-15 was written to apply to all serial numbers of all models. A design change was made in this area beginning with serial number 10175 of the Model AG-5B airplanes. Therefore, FAA determined that the action should not apply to Model AG-5B airplanes with a serial number of 10175 or higher.
Has FAA taken any action to this point? 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 Tiger Aircraft LLC (Type Certificate A16EA formerly held by American General Aircraft Corporation and Grumman American Aviation Corporation) Models AA-5, AA- 5A, AA-5B, and AG-5B airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on May 19, 2005 (70 FR 28854). The NPRM proposed to retain all the actions of AD 95-19-15 for all airplanes originally affected, but proposed to cut off the applicability for the Model AG-5B airplanes at serial number 10174.
Comments
Was the public invited to comment? We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA's response to each comment:
Comment Issue No. 1: Type Certificate Data Sheet (TCDS) Number (No.) Is Referenced Incorrectly in the NPRM
What is the commenter's concern? A letter from Tiger Aircraft LLC notes that the TCDS No. A16EH in the NPRM is referenced incorrectly. The TCDS should be No. A16EA.
What is FAA's response to the concern? We concur. We will correct all reference in the final rule of the TCDS to No. A16EA.
Comment Issue No. 2: Manufacturer's Contact Information Is Incorrect in the NPRM
What is the commenter's concern? The commenter from Tiger Aircraft LLC requests that FAA change the contact information to that for Tiger Aircraft LLC. American General Aircraft Corporation is out of business.
What is FAA's response to the concern? The FAA concurs. We will change the contact information in the final rule to show Tiger Aircraft LLC.
Conclusion
What is FAA's final determination on this issue? We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for the changes discussed above and minor editorial corrections. We have
[[Page 48858]]
determined that these changes and 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.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD affects 3,700 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the affected airplanes? We estimate the following costs to do this inspection:
Labor cost
Parts cost
Total cost per airplane
Total cost on U.S. operators
10 work hours x $65 = $650............... Not included..................
$650 3,700 x $650 = $2,405,000
We have no way of determining the number of airplanes that may need this replacement of any damaged bolts or repair as a result of the inspection.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action? 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
Will this AD impact various entities? 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.
Will this AD involve a significant rule or regulatory action? 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-2005-20968; Directorate Identifier 94-CE-15-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) 95-19-15, Amendment 39-9377 (60 FR 48628, September 20, 1995), and by adding a new AD to read as follows:
95-19-15 R1 Tiger Aircraft LLC: (Type Certificate A16EA formerly held by American General Aircraft Corporation and Grumman American Aviation Corporation): Amendment 39-14222; Docket No. FAA-2005- 20968; Directorate Identifier 94-CE-15-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on October 3, 2005.
What Other ADs Are Affected By This Action?
(b) This AD revises AD 95-19-15, Amendment 39-9377.
What Airplanes Are Affected by This AD?
(c) This AD affects the following airplane models and serial numbers that are certificated in any category:
Model
Serial numbers
AA-5........................... All Serial Numbers. AA-5A.......................... All Serial Numbers. AA-5B.......................... All Serial Numbers. AG-5B.......................... 99998, 10000 through 10174.
What Is the Unsafe Condition Presented in This AD?
(d) AD 95-19-15 currently requires you to inspect the wing attach shoulder bolts for fretting, scoring, wear, or enlarged or elongated mounting holes (known as damage from hereon); replace any damaged parts; repair any damaged areas; inspect the wing spar at the center spar clearance gap for excessive clearance; and shim the spar if excessive clearance is found. That AD was written to apply to all serial numbers of all models. A design change was made in this area beginning with serial number 10175 of the Model AG-5B airplanes. Therefore, the action should not apply to Model AG-5B airplanes with a serial number of 10175 or higher. This AD retains all the actions of AD 95-19-15 for all airplanes originally affected, but cuts off the applicability for the Model AG-5B airplanes at serial number 10174. We are issuing this AD to continue to prevent wing attach shoulder bolt failure, which, if not detected and corrected, could lead to structural damage of the wing/fuselage to the point of failure.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following, unless already done:
[[Page 48859]]
Actions
Compliance
Procedures
(1) Inspect any inboard wing Within the next 100 Follow American attach shoulder bolt for: hours aircraft time- General Aircraft in-service (TIS) Corporation Service after November 17, Bulletin No. SB-185- 1995 (the effective A, Revision A, date of AD 95-19- dated January 10, 15, unless already 2005. done
(i) Fretting, scoring, or wear (removal of the cad plating) to the shoulder of the bolt
(ii) A smooth machined area between the threads and the shoulder bevel of the shoulder bolt profile (2) Replace any inboard wing Before further
Follow American attach shoulder bolt with flight after the General Aircraft wear (removal of the cad inspection required Corporation Service plating from the shoulder by paragraph (e)(1) Bulletin No. SB-185- of the bolt) or if the
of this AD
A, Revision A, threads contact the
dated January 10, shoulder of the bolt found
2005. during the inspections required in paragraph (e)(1) of this AD (3) Inspect the mounting Within the next 100 Follow American holes in the wing spar and hours aircraft time- General Aircraft the center section spar for in-service (TIS) Corporation Service enlargement or elongation after November 17, Bulletin No. SB-185- that exceeds the specified 1995 (the effective A, Revision A, dimension
date of AD 95-19- dated January 10, 15), unless already 2005. done (4) Ream and bush any
Before further
Follow American mounting hole that exceeds flight after the General Aircraft the specified dimension inspection required Corporation Service found during the inspection by paragraph (e)(3) Bulletin No. SB-185- required by paragraph
of this AD
A, Revision A, (e)(3) of this AD
dated January 10, 2005 (5) Inspect the wing spar at Before further
Follow American the center spar clearance flight after the General Aircraft gap for excessive
inspections
Corporation Service clearance, and shim the required by
Bulletin No. SB-185- spar if excessive clearance paragraphs (e)(1) A, Revision A, is found
and (e)(3) of this dated January 10, AD
2005. (6) Do not install any wing As of October 3, Not Applicable. attach shoulder bolt that 2005 (the effective has wear resulting in
date of this AD) removal of the cad plating from the shoulder of the bolt or if the threads contact the shoulder bevel of the shoulder bolt profile
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, New York Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Richard Beckwith, Aerospace Engineer, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-794-5531; facsimile: 516-794-5531.
Does This AD Incorporate Any Material by Reference?
(g) You must do the actions required by this AD following the instructions in American General Aircraft Corporation Service Bulletin No. SB-185-A, Revision A, dated January 10, 2005. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Tiger Aircraft LLC, 226 Pilot Way, Martinsburg, WV 25401. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. 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-2005-20968; Directorate
Identifier 94-CE-15-AD.
Issued in Kansas City, Missouri, on August 11, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 05-16260 Filed 8-19-05; 8:45 am]
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