Federal Register, Volume 75 Issue 170 (Thursday, September 2, 2010)

[Federal Register Volume 75, Number 170 (Thursday, September 2, 2010)]
[Rules and Regulations]
[Pages 53846-53849]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-21725]

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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:

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:

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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