[Federal Register Volume 70, Number 161 (Monday, August 22, 2005)]
[Rules and Regulations]
[Pages 48857-48859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-16260]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[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.

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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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