Document ID: FAA-2010-1163-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: 328 Support Services GmbH, etc. Model 328-100 and -300 Airplanes
Posted Date: 2010-12-02T05:00Z

[Federal Register: December 2, 2010 (Volume 75, Number 231)]
[Proposed Rules]               
[Page 75159-75162]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02de10-5]                         

[[Page 75159]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1163; Directorate Identifier 2009-NM-233-AD]
RIN 2120-AA64

 
Airworthiness Directives; 328 Support Services GmbH (Type 
Certificate Previously Held by AvCraft Aerospace GmbH; Fairchild 
Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and -300 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede 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:

    During a routine inspection, cracks have been found on an 
aeroplane at the lower wing panel rear trailing edge inboard of flap 
lever arm 1 (rib 5). A subsequent inspection of the other aeroplanes 
in that operator's fleet revealed several more aeroplanes with 
cracks at the same location. This condition, if not corrected, could 
lead to structural failure of the affected wing panel, possibly 
resulting in the wing separating from the airplane with consequent 
loss of control.
* * * * *
    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 January 18, 
2011.

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 W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 328 
Support Services GmbH, Global Support Center, P.O. Box 1252, D-82231 
Wessling, Federal Republic of Germany; telephone +49 8153 88111 6666; 
fax +49 8153 88111 6565; e-mail gsc.op@328support.de; Internet http://
www.328support.de. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
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 Operations 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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1137; fax (425) 227-1149.

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-2010-1163; 
Directorate Identifier 2009-NM-233-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 based on those comments.
    We will post all comments we receive, without change, to http://
www.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 June 3, 2008, we issued AD 2008-10-51, Amendment 39-15535 (73 FR 
30752, May 29, 2008). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 2008-10-51, additional inspections and a 
modification have been developed to address the onset of cracks in the 
affected wing panel. The European Aviation Safety Agency (EASA), which 
is the Technical Agent for the Member States of the European Community, 
has issued Airworthiness Directive 2009-0194, dated September 1, 2009 
(referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    During a routine inspection, cracks have been found on an 
aeroplane at the lower wing panel rear trailing edge inboard of flap 
lever arm 1 (rib 5). A subsequent inspection of the other aeroplanes 
in that operator's fleet revealed several more aeroplanes with 
cracks at the same location. This condition, if not corrected, could 
lead to structural failure of the affected wing panel, possibly 
resulting in the wing separating from the airplane with consequent 
loss of control.
    To correct this unsafe condition, EASA issued Emergency AD 2008-
0087-E [dated May 8, 2008] to require detailed visual inspections 
(DVI) of both the left (LH) and right (RH) wing panel rear trailing 
edge around rib 3 and rib 5 and a subsequent Eddy Current inspection 
(NDI) [non-destructive inspection] of the same area to detect 
cracks, follow-up repair actions when cracks are found, and the 
reporting of all findings. The TC [type certificate] holder has now 
developed a modification, consisting of the cold expansion of the 
former lower wing panel CAMLOC holes together with the installation 
of new attachment material that will prevent the onset of cracks in 
the affected wing panel.
    For the reasons described above, this [EASA] AD retains the 
inspection and repair requirements of AD 2008-0087-E, which is 
superseded, adds repetitive inspections and a requirement to modify 
both the LH and RH wing panel rear trailing edges from rib 3 to rib 
9. Modification does not constitute terminating action for the new 
repetitive inspection requirements of this AD.

    The new inspections are repetitive eddy current inspections. The 
modification includes cold expansion of the former lower wing panel 
CAMLOC holes and installation of new attachment material. You may 
obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

    328 Support Services GmbH has issued Alert Service Bulletins ASB-
328-57-037 and ASB-328J-57-015, both Revision 2, both dated May 20, 
2008. 328 Support Services GmbH has also issued Service Bulletins SB-
328-57-481 and SB-328J-57-230, both Revision 1, both dated October 15, 
2009. The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

[[Page 75160]]

FAA's Determination and Requirements of This 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 the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

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 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

    Based on the service information, we estimate that this proposed AD 
would affect about 49 products of U.S. registry.
    The actions that are required by AD 2008-10-51 and retained in this 
proposed AD take about 2 work-hours per product, at an average labor 
rate of $85 per work hour. Required parts cost about $0 per product. 
Based on these figures, the estimated cost of the currently required 
actions is $170 per product.
    We estimate that it would take about 8 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about 
$11,600 per product. Where the service information lists required parts 
costs that are covered under warranty, we have assumed that there will 
be no charge for these costs. As we do not control warranty coverage 
for affected parties, some parties may incur costs higher than 
estimated here. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $601,720, or $12,280 per product.

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 39-15535 (73 FR 
30752, May 29, 2008) and adding the following new AD:

328 Support Services GmbH (Type Certificate Previously Held by 
AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt 
GmbH): Docket No. FAA-2010-1163; Directorate Identifier 2009-NM-233-
AD.

Comments Due Date

    (a) We must receive comments by January 18, 2011.

Affected ADs

    (b) This AD supersedes AD 2008-10-51, Amendment 39-15535.

Applicability

    (c) This AD applies to 328 Support Services GmbH (Type 
Certificate previously held by AvCraft Aerospace GmbH; Fairchild 
Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and -300 
airplanes; all serial numbers; certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

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

    During a routine inspection, cracks have been found on an 
aeroplane at the lower wing panel rear trailing edge inboard of flap 
lever arm 1 (rib 5). A subsequent inspection of the other aeroplanes 
in that operator's fleet revealed several more aeroplanes with 
cracks at the same location. This condition, if not corrected, could 
lead to structural failure of the affected wing panel, possibly 
resulting in the wing separating from the airplane with consequent 
loss of control.
* * * * *
    The new inspections are repetitive eddy current inspections. The 
modification includes cold expansion of the former lower wing panel 
CAMLOC holes and installation of new attachment material.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2008-10-51 With Updated Service 
Information

Repetitive Detailed Visual Inspections for Cracks

    (g) Within 10 flight cycles, or 10 flight hours, or 7 days, 
whichever occurs first, after June 3, 2008 (the effective date of AD 
2008-10-51): Accomplish a detailed visual inspection of both the 
left-hand (LH) and right-hand (RH) lower wing panel inboard and 
outboard of flap lever arm 1 (rib 5) for cracks, in accordance with 
the Accomplishment Instructions of Dornier Alert Service Bulletin 
ASB-328J-57-015 or

[[Page 75161]]

ASB-328-57-037, both Revision 1, both dated May 8, 2008, as 
applicable; or 328 Support Services Alert Service Bulletin ASB-328J-
57-015 or ASB-328-57-037, both Revision 2, both dated May 20, 2008; 
as applicable. After the effective date of this AD, use only 328 
Support Services Alert Service Bulletin ASB-328J-57-015 or ASB-328-
57-037, both Revision 2, both dated May 20, 2008. If no crack is 
detected, repeat the detailed visual inspection thereafter at 
intervals not to exceed 50 flight hours. If any crack is detected, 
before further flight, do an eddy current inspection in accordance 
with paragraph (h) of this AD.

Repetitive Eddy Current Inspections for Cracks

    (h) Within 400 flight hours or 3 months after June 3, 2008, 
whichever occurs first: Accomplish an eddy current inspection of 
both the LH and RH lower wing panel in the vicinity of rib 3 and 
inboard and outboard of flap lever arm 1 (rib 5) for cracks, in 
accordance with the Accomplishment Instructions of Dornier Alert 
Service Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 1, 
both dated May 8, 2008; or 328 Support Services Alert Service 
Bulletin ASB-328J-57-015 or ASB-328-57-037, both Revision 2, both 
dated May 20, 2008; as applicable. After the effective date of this 
AD, use only 328 Support Services Alert Service Bulletin ASB-328J-
57-015 or ASB-328-57-037, both Revision 2, both dated May 20, 2008. 
Repeat the eddy current inspection thereafter at intervals not to 
exceed 400 flight cycles until the inspection required by paragraph 
(i) of this AD is accomplished. Accomplishment of the eddy current 
inspection terminates the detailed visual inspection required by 
paragraph (g) of this AD.

New Requirements of This AD

New Repetitive Intervals for Eddy Current Inspections

    (i) Within 800 flight cycles after the last eddy current 
inspection required in paragraph (h) of this AD is done, or within 
60 days after the effective date of this AD, whichever occurs later, 
do an eddy current inspection for cracking of the lower wing panel 
(outside) around the flap lever arm 1 (rib 5); in accordance with 
the Accomplishment Instructions of 328 Support Services Alert 
Service Bulletin ASB-328-57-037 (for Model 328-100 airplanes) or 
ASB-328J-57-015 (for Model 328-300 airplanes), both Revision 2, both 
dated May 20, 2008. Repeat the inspection thereafter at intervals 
not to exceed 800 flight cycles. Doing this inspection terminates 
the repetitive inspection requirements of paragraph (h) of this AD.

Inspection and Modification of Lower Wing Panel

    (j) Within 24 months after the effective date of this AD, do an 
eddy current inspection of the lower wing panel (outside) around the 
flap lever arm 1 (rib 5). If no cracking is found, modify the lower 
wing panel by doing a cold expansion of the CAMLOC holes and 
installing new attachment material from rib 9 LH to rib 9 RH. Do all 
actions required by this paragraph in accordance with the 
Accomplishment Instructions of 328 Support Services Service Bulletin 
SB-328-57-481 (for Model 328-100 airplanes) or SB-328J-57-230 (for 
Model 328-300 airplanes), both Revision 1, both dated October 15, 
2009. Doing the modification does not end the repetitive inspection 
requirements of paragraph (i) of this AD.

Repair

    (k) If any cracking is found during any inspection required by 
this AD, before further flight contact 328 Support Services GmbH for 
repair instructions and do the repair using a method approved by 
either the Manager, International Branch, ANM 116, Transport 
Airplane Directorate, FAA; or European Aviation Safety Agency (EASA) 
(or its delegated agent).

Inspections Accomplished According to Previous Issues of Service 
Bulletins

    (l) Inspections accomplished before the effective date of this 
AD according to Dornier Alert Service Bulletin ASB-328-57-037 or 
Dornier Alert Service Bulletin ASB 328J-57-015, both Revision 1, 
both dated May 8, 2008, as applicable, are considered acceptable for 
compliance with the inspection requirements of paragraphs (i) and 
(j) of this AD.

Report

    (m) At the applicable time specified in paragraph (m)(1) and 
(m)(2) of this AD: Send 328 Support Services GmbH a report of 
findings (both positive and negative) found during each inspection 
required by paragraphs (g), (h), and (i) of this AD. The report must 
include the inspection results, a description of any cracks found, 
the airplane serial number, and the number of landings and flight 
hours on the airplane. Send the report to 328 Support Services GmbH, 
Global Support Center, P.O. Box 1252, D-82231 Wessling, Federal 
Republic of Germany; Telephone +49 8153 88111 6666; fax 49 8153 
88111 6565; e-mail: gsc.op@328support.de.
    (1) For any inspection done after the effective date of this AD: 
Within 30 days after the inspection.
    (2) For any inspection done before the effective date of this 
AD: Within 30 days after the effective date of this AD.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows:
    EASA AD 2009-0194 gives credit for eddy current inspections 
conducted in accordance with the maintenance review board tasks. We 
are not giving credit for those inspections.

Other FAA AD Provisions

    (n) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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: Tom 
Rodriguez, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (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: A Federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave., 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.
    (4) Special Flight Permits: Special flight permits may be issued 
in accordance with sections 21.197 and 21.199 of the Federal 
Aviation Regulations (14 CFR 21.197 and 21.199) to operate the 
airplane to a location where the requirements of paragraphs (g), 
(h), and (i) of this AD can be done if the following conditions are 
met:
    (i) The initial inspection required by paragraph (g) of this AD 
must be accomplished.
    (ii) If a crack indication exceeds 12.5 mm (0.49 inch), the 
Manager, International Branch, ANM-116, concurs with issuance of the 
special flight permits.

Related Information

    (o) Refer to MCAI EASA Airworthiness Directive 2009-0194, dated 
September 1, 2009, and the service bulletins listed in Table 1 of 
this AD, for related information.

[[Page 75162]]

                       Table 1--Service Bulletins
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        Service Bulletin           Revision              Date
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328 Support Services Alert                2  May 20, 2008.
 Service Bulletin ASB-328-57-037.
328 Support Services Alert                2  May 20, 2008.
 Service Bulletin ASB-328J-57-
 015.
328 Support Services Service              1  October 15, 2009.
 Bulletin SB-328-57-481.
328 Support Services GmbH                 1  October 15, 2009.
 Service Bulletin SB-328J-57-230.
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    Issued in Renton, Washington on November 22, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-30282 Filed 12-1-10; 8:45 am]
BILLING CODE 4910-13-P