[Federal Register Volume 76, Number 182 (Tuesday, September 20, 2011)]
[Unknown Section]
[Pages 58094-58098]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-22032]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1163; Directorate Identifier 2009-NM-233-AD;
Amendment 39-16795; AD 2011-18-13]
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), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
that applies to the products listed above. This 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.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective October 25, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 25,
2011.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
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:
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 December 2, 2010 (75
FR 75159), and proposed to supersede AD 2008-10-51, Amendment 39-15535
(73 FR 30752, May 29, 2008). That NPRM proposed 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 [European Aviation Safety
Agency] 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 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.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
MCAI Reference Updates
EASA issued AD 2009-0194R1 on March 10, 2011, which was corrected
on March 22, 2011. References have been updated in Note 1 and paragraph
(p) of this AD to include this revision.
[[Page 58095]]
Request to Remove Repetitive Inspection Interval From Paragraph (h) of
This AD
Garner CAD Technic Design Organization (GCT DO) Airworthiness
Office requested that the 400-flight-cycle repetitive inspection
interval be removed from paragraph (h) of the NPRM (75 FR 75159,
December 2, 2010). GCT DO Airworthiness Office stated that, based on
fatigue data, this repetitive inspection is not required, and is not
specified in revised EASA AD 2009-0194R1, dated March 10, 2011, and
corrected on March 22, 2011.
We agree. Based on fatigue data, we have determined that the 400-
flight-cycle repetitive inspection interval should be removed from
paragraph (h) of this AD. The repetitive inspection was removed from
revised EASA AD 2009-0194R1, dated March 10, 2011, and corrected on
March 22, 2011. Paragraph (h) of this AD has been changed accordingly.
References to the 400-flight-cycle repetitive inspections also were
removed from paragraphs (i) and (j) of this AD.
To ensure that operators get credit for the most recent inspection
done in accordance with 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; we have clarified
paragraph (g) of this AD. We have replaced the phrase, ``in accordance
with the requirements of paragraph (h) of this AD,'' with the phrase,
``in accordance with 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.''
Request for Extended Inspection Interval in Paragraph (i) of This AD
GCT DO Airworthiness Office requested that the initial compliance
time and repetitive inspection interval defined in paragraph (i) of the
NPRM (75 FR 75159, December 2, 2010) be extended from 800 flight cycles
to 1,500 flight cycles. GCT DO Airworthiness Office stated that this
extension has been allowed based on fatigue data, and was specified in
revised EASA AD 2009-0194R1, dated March 10, 2011, and corrected on
March 22, 2011.
We agree to extend the initial compliance time and repetitive
inspection intervals for the reasons given by the commenter. Paragraph
(i) of this AD has been changed accordingly.
Request To Extend Threshold for Post-Modification Inspections
GCT DO Airworthiness Office requested that based on fatigue data,
the threshold for the post-modification initial inspection be extended
from 800 flight cycles to 25,000 flight cycles for the Model 328-100
airplane, and from 800 flight cycles to 20,000 flight cycles for Model
328-300 airplanes, and that the repetitive inspections be extended from
800 flight cycles to 1,500 flight cycles.
We agree to extend the threshold for post-modification initial
inspections as requested. Based on fatigue data, the referenced EASA AD
has included these extensions; therefore, we have added paragraph (k)
to the AD to include the new compliance times.
Additional Change to NPRM
The NPRM (75 FR 75159, December 2, 2010) would have allowed
issuance of a special flight permit if a crack was found that
``exceeds'' 12.5 mm (0.49 inch). We have changed paragraph (o)(4)(ii)
of this AD to change the wording from ``exceeds'' to ``is less than or
equal to.''
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
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 our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 49 products of U.S.
registry.
The actions that are required by AD 2008-10-51 and retained in this
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 will take about 8 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will 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 parts. 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 this AD to the
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 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 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
[[Page 58096]]
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 Operations office
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 Operations 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
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]
2. The FAA amends Sec. 39.13 by removing Amendment 39-15535 (73 FR
30752, May 29, 2008) and adding the following new AD:
2011-18-13 328 Support Services GmbH (Type Certificate
Previously Held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH;
Dornier Luftfahrt GmbH): Amendment 39-16795. Docket No. FAA-2010-
1163; Directorate Identifier 2009-NM-233-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
25, 2011.
Affected ADs
(b) This AD supersedes AD 2008-10-51, Amendment 39-15535 (73 FR
30752, May 29, 2008).
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 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 (73 FR 30752, May 29,
2008), With Updated Service Information and Removal of Certain
Repetitive Inspections
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 (73 FR 30752, May 29, 2008)): 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 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, as applicable. 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 Dornier Alert Service Bulletin ASB-328J-57-015 or 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.
Eddy Current Inspections for Cracks
(h) Except as required by paragraph (g) of this AD, within 400
flight hours or 3 months after June 3, 2008, whichever occurs first:
Accomplish an eddy current inspection for cracking 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), 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, 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, as
applicable. 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 1,500 flight cycles after the most recent eddy
current inspection done in accordance with the applicable service
bulletin listed in table 1 of this AD, 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 1,500 flight cycles, except as provided by paragraph (k) of
this AD.
Table 1--Service Bulletins
------------------------------------------------------------------------
Service Bulletin Revision Date
------------------------------------------------------------------------
Dornier Alert Service 1 May 8, 2008.
Bulletin ASB-328-57-037.
Dornier Alert Service 1 May 8, 2008.
Bulletin ASB-328J-57-015.
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.
------------------------------------------------------------------------
[[Page 58097]]
Inspection and Modification of Lower Wing Panel
(j) Within 24 months after the effective date of this AD, do an
eddy current inspection for cracking of the lower wing panel
(outside) around the flap lever arm 1 (rib 5). If no cracking is
found, within 24 months after the effective date of this AD, 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.
(k) After the modification required by paragraph (j) is done, do
the eddy current inspection required by paragraph (i) of this AD at
the applicable time specified in paragraph (k)(1) or (k)(2) of this
AD. Repeat the inspections thereafter at the intervals specified in
paragraph (i) of this AD.
(1) For Model 328-100 airplanes: Within 25,000 flight cycles
after accomplishing the modification specified in paragraph (j) of
this AD.
(2) For Model 328-300 airplanes: Within 20,000 flight cycles
after accomplishing the modification specified in paragraph (j) of
this AD.
Repair
(l) 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
(m) 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
(n) At the applicable times specified in paragraphs (n)(1) and
(n)(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), (i), and (j) 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: [email protected].
(1) For any inspection done on or 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 Airworthiness Directive 2009-0194R1, dated March 10, 2011,
corrected March 22, 2011, 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
(o) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office as
appropriate. If sending information directly to the International
Branch, send it 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. Information may be e-mailed to:
[email protected]. Before using any approved AMOC,
notify your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding 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), (i), (j), (k), and (l) 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 is less than or equal to 12.5 mm
(0.49 inch), the Manager, International Branch, ANM-116, concurs
with issuance of the special flight permits.
Related Information
(p) Refer to MCAI EASA Airworthiness Directive 2009-0194R1,
dated March 10, 2011, corrected March 22, 2011, and the service
bulletins listed in table 2 of this AD, for related information.
Table 2--Related Service Bulletins
------------------------------------------------------------------------
Service Bulletin Revision Date
------------------------------------------------------------------------
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.
------------------------------------------------------------------------
Material Incorporated by Reference
(q) You must use the service information contained in table 3 of
this AD to do the actions required by this AD, as applicable, unless
the AD specifies otherwise.
[[Page 58098]]
Table 3--All Material Incorporated by Reference
------------------------------------------------------------------------
Service Bulletin Revision Date
------------------------------------------------------------------------
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.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this 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 [email protected]; Internet
http://www.328support.de.
(3) You may review copies of the 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.
(4) You may also review copies of the service information that
is incorporated by reference 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 Renton, Washington, on August 19, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-22032 Filed 9-19-11; 8:45 am]
BILLING CODE 4910-13-P