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

As Enacted ( Federal Register)

Cited authorities 2

Cited in

Federal Register: June 21, 2010 (Volume 75, Number 118)

Proposed Rules

Page 34953-34956

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

DOCID:fr21jn10-21

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 14 CFR Part 39

Docket No. FAA-2010-0463; Directorate Identifier 2010-CE-021-AD

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: Notice of proposed rulemaking (NPRM).

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would revise an existing AD. This proposed

AD results from mandatory continuing airworthiness information (MCAI) originated 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

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aircraft has revealed cracks in the Horizontal Stabilizer rear spar splice plate and inboard main ribs around the area of the Horizontal

Stabilizer 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 proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by August 5, 2010.

ADDRESSES: You may send comments by any of the following methods:

Federal eRulemaking Portal: Go to http:// www.regulations.gov. Follow the instructions for submitting comments.

Fax: (202) 493-2251.

Mail: U.S. Department of Transportation, Docket

Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New

Jersey Avenue, SE., Washington, DC 20590.

Hand Delivery: U.S. Department of Transportation, Docket

Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New

Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,

Monday through Friday, except Federal holidays.

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 this proposed AD, 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.

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:

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0463;

Directorate Identifier 2010-CE-021-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments.

We will post all comments we receive, without change, to http:// regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

On April 20, 2010, we issued AD 2010-10-01, Amendment 39-16280 (75

FR 23577, May 4, 2010). That AD required actions intended to address an unsafe condition on the products listed above.

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 proposing to revise 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 SB. This proposed revision of the FAA's AD will make the FAA AD more in line with the latest version of the received MCAI.

The Civil Aviation Safety Authority (CASA), which is the aviation authority for Australia, has issued AD/GA8/5, Amdt 4, dated May 11, 2010 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:

Inspection of a high time aircraft has revealed cracks in the

Horizontal Stabilizer rear spar splice plate and inboard main ribs around the area of the Horizontal Stabilizer 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 stabilizers 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.

You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Gippsland Aeronautics has issued Mandatory Service Bulletin SB-GA8- 2002-02, Issue 6, dated April 21, 2010. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.

Differences Between This Proposed 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 proposed 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 proposed AD.

Costs of Compliance

We estimate that this proposed AD will affect 25 products of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product.

Based on these figures, we estimate the cost of the proposed AD on

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.

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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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the

Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES 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] 2. The FAA amends Sec. 39.13 by removing Amendment 39-16280 (75 FR 23577, May 4, 2010), and adding the following new AD:

GA 8 Airvan (Pty) Ltd.: Docket No. FAA-2010-0463; Directorate

Identifier 2010-CE-021-AD.

Comments Due Date

(a) We must receive comments by August 5, 2010.

Affected ADs

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

Applicability

(1) Group 1 Airplanes (retains the actions and applicability from AD 2009-05-01): Model GA8 airplanes, serial numbers GA8-00-004 and up; and

(2) 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.

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 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.

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(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):