Document ID: FAA-2010-0463-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: GA 8 Airvan (Pty) Ltd Models GA8 and GA8 TC320 Airplanes
Posted Date: 2010-09-02T04:00Z

[Federal Register: September 2, 2010 (Volume 75, Number 170)]
[Rules and Regulations]               
[Page 53846-53849]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02se10-4]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0463; Directorate Identifier 2010-CE-021-AD; 
Amendment 39-16425; AD 2010-10-01 R1]
RIN 2120-AA64

 
Airworthiness Directives; GA 8 Airvan (Pty) Ltd Models GA8 and 
GA8-TC320 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are revising an existing airworthiness directive (AD) for 
the products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    Inspection of a high time aircraft has revealed cracks in the 
Horizontal Stabiliser rear spar splice plate and inboard main ribs 
around the area of the Horizontal Stabiliser rear pivot attachment. 
Additionally, failure of some attach bolts in service may be due to 
improper assembly.
    This amendment is issued to include an applicability matrix 
(Table 1, page 2) in the compliance section of the service bulletin 
for improved clarity.

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective October 7, 2010.
    On October 7, 2010, the Director of the Federal Register approved 
the incorporation by reference of Gippsland Aeronautics Mandatory 
Service Bulletin SB-GA8-2002-02, Issue 6, dated April 21, 2010, listed 
in this AD.
    As of March 2, 2009 (74 FR 8159; February 24, 2009), the Director 
of the Federal Register approved the incorporation by reference of 
Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 
5, dated November 13, 2008, listed in this AD.

ADDRESSES: You may examine the AD docket on the Internet at http://
www.regulations.gov or in person at the Docket Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; fax: (816) 329-4090.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 21, 2010 (75 FR 
34953), and proposed to revise AD 2010-10-01, Amendment 39-16280 (75 FR 
23577, May 4, 2010).
    Since we issued AD 2010-10-01, the foreign authority has issued an 
amendment to include an applicability matrix in the compliance section 
of the manufacturer's service bulletin for improved clarity. The FAA is 
revising this AD to allow the use of issue 6 or issue 5 of the service 
bulletin. An operator would be in compliance if the operator chose to 
only accomplish issue 5 of the service bulletin. This revision of the 
FAA's AD will make the FAA AD more in line with the latest version of 
the received MCAI.
    The NPRM proposed to correct an unsafe condition for the specified 
products. The MCAI states that:

    Inspection of a high time aircraft has revealed cracks in the 
Horizontal Stabiliser rear spar splice plate and inboard main ribs 
around the area of the Horizontal Stabiliser rear pivot attachment. 
Additionally, failure of some attach bolts in service may be due to 
improper assembly.
    This amendment is issued to include an applicability matrix 
(Table 1, page 2) in the compliance section of the service bulletin 
for improved clarity.
    The previous amendment included reference to the GA8-TC 320 
variant in the applicability section.
    Amendment 2 was issued because the requirement document now 
contains an inspection for cracking in horizontal stabilisers which 
have load transferring fittings installed.
    Previous amendments of this AD listed the AD requirements in 
full. Due to the extensive

[[Page 53847]]

use of diagrams and photographs, it is no longer appropriate or 
practical to write the requirements of the service bulletin out in 
full in this AD. All requirements, accomplishment instructions and 
illustrations are contained in the service bulletin.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a note within the AD.

Costs of Compliance

    We estimate that this AD will affect 25 products of U.S. registry. 
We also estimate that it will take about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts will cost about $0 per product.
    Based on these figures, we estimate the cost of this AD to the U.S. 
operators to be $2,125 or $85 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 5 work-hours and require parts costing $200, for a cost of 
$625 per product. We have no way of determining the number of products 
that may need these actions.

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 
rulemaking action.

Regulatory Findings

    We 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD Docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone (800) 647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

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 FAA amends 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 Amendment 39-16280 (75 FR 
23577, May 4, 2010) and adding the following new AD:

2010-10-01 R1 GA 8 Airvan (Pty) Ltd.: Amendment 39-16425; Docket No. 
FAA-2010-0463; Directorate Identifier 2010-CE-021-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
7, 2010.

Affected ADs

    (b) This AD revises AD 2010-10-01, Amendment 39-16280.

Applicability

    (c) This AD applies to the following model and serial number 
airplanes, certificated in any category:
    (i) Group 1 Airplanes (retains the actions and applicability 
from AD 2009-05-01): Model GA8 airplanes, serial numbers GA8-00-004 
and up; and
    (ii) Group 2 Airplanes: Model GA8-TC320 airplanes, all serial 
numbers.

Subject

    (d) Air Transport Association of America (ATA) Code 55: 
Stabilizers.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Inspection of a high time aircraft has revealed cracks in the 
Horizontal Stabiliser rear spar splice plate and inboard main ribs 
around the area of the Horizontal Stabiliser rear pivot attachment. 
Additionally, failure of some attach bolts in service may be due to 
improper assembly.
    This amendment is issued to include an applicability matrix 
(Table 1, page 2) in the compliance section of the service bulletin 
for improved clarity.
    The previous amendment included reference to the GA8-TC 320 
variant in the applicability section.
    Amendment 2 was issued because the requirement document now 
contains an inspection for cracking in horizontal stabilisers which 
have load transferring fittings installed.
    Previous amendments of this AD listed the AD requirements in 
full. Due to the extensive use of diagrams and photographs, it is no 
longer appropriate or practical to write the requirements of the 
service bulletin out in full in this AD. All requirements, 
accomplishment instructions and illustrations are contained in the 
service bulletin.

The FAA is revising AD 2010-10-01 to allow the use of issue 6 or 
issue 5 of the service bulletin. An operator is in compliance if the 
operator chooses to only accomplish issue 5

[[Page 53848]]

of the SB. This proposed revision of the FAA's AD will make the FAA 
AD more consistent with the latest version of the MCAI.

Actions and Compliance

    (f) For Group 1 Airplanes: Unless already done, do the following 
actions:
    (1) Within the next 10 hours time-in-service (TIS) after March 
2, 2009 (the effective date retained from AD 2009-05-01):
    (i) For all aircraft not incorporating computer numeric control 
(CNC) machined elevator hinges, inspect and repair the left and 
right horizontal stabilizer rear pivot attachment installation 
following instruction ``3. Rear Pivot Attachment Inspection,'' of 
Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, 
Issue 5, dated November 13, 2008; or Gippsland Aeronautics Mandatory 
Service Bulletin SB-GA8-2002-02, Issue 6, dated April 21, 2010; and
    (ii) For all aircraft, inspect the left and right rear attach 
bolt mating surfaces for damage or an out of square condition and 
replace the left and right rear attach bolts following instruction 
``5. Rear Attach Bolt Replacement,'' of Gippsland Aeronautics 
Mandatory Service Bulletin SB-GA8-2002-02, Issue 5, dated November 
13, 2008; or Gippsland Aeronautics Mandatory Service Bulletin SB-
GA8-2002-02, Issue 6, dated April 21, 2010. Reworking the mating 
surfaces by spotfacing is no longer acceptable. If the mating 
surfaces are damaged, not square, or were previously reworked by 
spotfacing the surface, replace the parts as specified in Gippsland 
Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 5, 
dated November 13, 2008; or Gippsland Aeronautics Mandatory Service 
Bulletin SB-GA8-2002-02, Issue 6, dated April 21, 2010.
    (2) Within the next 10 hours TIS after March 2, 2009 (the 
effective date retained from AD 2009-05-01) and repetitively 
thereafter at intervals not to exceed 100 hours TIS or 12 months, 
whichever occurs first, for all aircraft:
    (i) Inspect the horizontal stabilizer externally following 
instruction ``2. External Inspection (Lower flange, Stabilizer rear 
spar),'' of Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-
2002-02, Issue 5, dated November 13, 2008; or Gippsland Aeronautics 
Mandatory Service Bulletin SB-GA8-2002-02, Issue 6, dated April 21, 
2010; and
    (ii) Inspect the horizontal stabilizer internally following 
instruction ``4. Internal Inspection,'' of Gippsland Aeronautics 
Mandatory Service Bulletin SB-GA8-2002-02, Issue 5, dated November 
13, 2008; or Gippsland Aeronautics Mandatory Service Bulletin SB-
GA8-2002-02, Issue 6, dated April 21, 2010.
    (3) If during the inspection required by paragraph (f)(2) of 
this AD any excessive local deflection or movement of the lower skin 
surrounding the lower pivot attachment, cracking, or working (loose) 
rivet is found, before further flight, obtain an FAA-approved repair 
scheme from the manufacturer and incorporate this repair scheme. Due 
to FAA policy, the repair scheme/modification for crack damage must 
include an immediate repair of the crack. The repair scheme cannot 
be by repetitive inspection only. The repair scheme/modification may 
incorporate repetitive inspections in addition to the repetitive 
inspections required in paragraph (f)(2) of this AD. Continued 
operational flight with un-repaired crack damage is not permitted.
    (g) For Group 2 Airplanes: Unless already done, do the following 
actions:
    (1) Within the next 10 hours TIS after May 10, 2010 (the 
effective date retained from AD 2010-10-01):
    (i) For all aircraft not incorporating computer numeric control 
(CNC) machined elevator hinges, inspect and repair the left and 
right horizontal stabilizer rear pivot attachment installation 
following instruction ``3. Rear Pivot Attachment Inspection,'' of 
Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, 
Issue 5, dated November 13, 2008; or Gippsland Aeronautics Mandatory 
Service Bulletin SB-GA8-2002-02, Issue 6, dated April 21, 2010; and,
    (ii) For all aircraft, inspect the left and right rear attach 
bolt mating surfaces for damage or an out of square condition and 
replace the left and right rear attach bolts following instruction 
``5. Rear Attach Bolt Replacement,'' of Gippsland Aeronautics 
Mandatory Service Bulletin SB-GA8-2002-02, Issue 5, dated November 
13, 2008; or Gippsland Aeronautics Mandatory Service Bulletin SB-
GA8-2002-02, Issue 6, dated April 21, 2010. Reworking the mating 
surfaces by spotfacing is no longer acceptable. If the mating 
surfaces are damaged, not square, or were previously reworked by 
spotfacing the surface, before further flight, replace the parts as 
specified in Gippsland Aeronautics Mandatory Service Bulletin SB-
GA8-2002-02, Issue 5, dated November 13, 2008; or Gippsland 
Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, Issue 6, 
dated April 21, 2010.
    (2) Within the next 10 hours TIS after May 10, 2010 (the 
effective date retained from AD 2010-10-01) and repetitively 
thereafter at intervals not to exceed 100 hours TIS or 12 months, 
whichever occurs first, for all aircraft:
    (i) Inspect the horizontal stabilizer externally following 
instruction ``2. External Inspection (Lower flange, Stabilizer rear 
spar),'' of Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-
2002-02, Issue 5, dated November 13, 2008; or Gippsland Aeronautics 
Mandatory Service Bulletin SB-GA8-2002-02, Issue 6, dated April 21, 
2010; and
    (ii) Inspect the horizontal stabilizer internally following 
instruction ``4. Internal Inspection,'' of Gippsland Aeronautics 
Mandatory Service Bulletin SB-GA8-2002-02, Issue 5, dated November 
13, 2008; or Gippsland Aeronautics Mandatory Service Bulletin SB-
GA8-2002-02, Issue 6, dated April 21, 2010.
    (3) If during the inspection required by paragraph (g)(2) of 
this AD any excessive local deflection or movement of the lower skin 
surrounding the lower pivot attachment, cracking, or working (loose) 
rivet is found, before further flight, obtain an FAA-approved repair 
scheme from the manufacturer and incorporate this repair scheme. Due 
to FAA policy, the repair scheme/modification for crack damage must 
include an immediate repair of the crack. The repair scheme cannot 
be by repetitive inspection only. The repair scheme/modification may 
incorporate repetitive inspections in addition to the repetitive 
inspections required in paragraph (g)(2) of this AD. Continued 
operational flight with un-repaired crack damage is not permitted.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows:

    (1) ``Requirement: 1. Daily Inspection (Stabilizer attach 
bolt)'' of the service information requires a daily inspection of 
the stabilizer attach bolt. The daily inspection is not a 
requirement of this AD. Instead of the daily inspection, we require 
you to perform, within 10 hours TIS, ``Requirement 3. Rear Pivot 
Attachment Inspection'' and ``Requirement 5. Rear Attachment Bolt 
Replacement'' of the service information. Compliance with 
requirement 3. and 5. is a terminating action for the daily 
inspection, and we are requiring these within 10 hours TIS after the 
effective date of AD 2009-05-01 for Group 1 airplanes and AD 2010-
10-01 for Group 2 airplanes.
    (2) ``Requirement: 2. External Inspection (Lower flange, 
Stabilizer rear spar)'' of the service information does not specify 
any action if excessive local deflection or movement of lower skin, 
cracking, or working (loose) rivet is found. We require obtaining 
and incorporating an FAA-approved repair scheme from the 
manufacturer before further flight.
    (3) The MCAI does not state if further flight with known cracks 
is allowed. FAA policy is to not allow further flight with known 
cracks in critical structure. We require that if any cracks are 
found when accomplishing the inspection required in paragraphs 
(f)(2) and (g)(2) of this AD, you must repair the cracks before 
further flight.
    (4) The service information does not state that parts with 
spotfaced nut and bolt mating surfaces require replacement. However, 
the service information no longer allows reworking of the mating 
surfaces by spotfacing. We require that if any nut and bolt surfaces 
were previously reworked by spotfacing, you must replace the parts.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; fax: (816) 329-4090. Before using 
any approved AMOC on any airplane to which the AMOC applies, notify 
your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO.

[[Page 53849]]

    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (h) Refer to MCAI Civil Aviation Safety Authority AD No. AD/GA8/
5, Amdt 4, dated May 11, 2010; Gippsland Aeronautics Mandatory 
Service Bulletin SB-GA8-2002-02, Issue 5, dated November 13, 2008; 
and Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, 
Issue 6, dated April 21, 2010, for related information.

Material Incorporated by Reference

    (h) You must use Gippsland Aeronautics Mandatory Service 
Bulletin SB-GA8-2002-02, Issue 5, dated November 13, 2008; and 
Gippsland Aeronautics Mandatory Service Bulletin SB-GA8-2002-02, 
Issue 6, dated April 21, 2010, 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 Gippsland Aeronautics Mandatory 
Service Bulletin SB-GA8-2002-02, Issue 6, dated April 21, 2010, 
under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On March 2, 2009 (74 FR 8159; February 24, 2009), the 
Director of the Federal Register previously approved the 
incorporation by reference of Gippsland Aeronautics Mandatory 
Service Bulletin SB-GA8-2002-02, Issue 5, dated November 13, 2008.
    (3) For service information identified in this AD, contact 
Gippsland Aeronautics, Attn: Technical Services, P.O. Box 881, 
Morwell Victoria 3840, Australia; telephone: + 61 03 5172 1200; fax: 
+61 03 5172 1201; Internet: http://www.gippsaero.com.
    (4) You may review copies of the service information 
incorporated by reference for this AD at the FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
Central Region, call (816) 329-3768.
    (5) You may also review copies of the service information 
incorporated by reference for this AD 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 August 25, 2010.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-21725 Filed 9-1-10; 8:45 am]
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