Airworthiness Directives:
Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)
Rules and Regulations
Pages 27246-27250
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
FR Doc No: 2011-10688
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA-2010-1273; Directorate Identifier 2010-NM-089-AD;
Amendment 39-16686; AD 2011-10-05
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-203, -204, -222, - 304, -322, and -324 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new airworthiness directive (AD) for 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:
A specific area, the lower tail plane cut-out located in the tail cone is subject to an inspection programme [for cracking] * *
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail cone. We are issuing this AD to require actions to correct the unsafe condition on these products.
DATES: This AD becomes effective June 15, 2011.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 15, 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; 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 January 3, 2011 (76
FR 46). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:
A specific area, the lower tail plane cut-out located in the tail cone is subject to an inspection programme specified in the
Airbus Service Bulletin (SB) A310-53-2074. EASA issued AD 2007-0053
which superseded French AD 1992-106-132 R6; French AD 1992-106-132 corresponds to FAA AD 98-26-01
to require the accomplishment of this SB at Revision 03.
Airbus has established that this SB needed to be revised in order to state correct threshold and intervals due to errors introduced at revision 03. Consequently, revision 04 of this SB has been issued, and opportunity was taken:
--To clarify the inspection area and associated threshold and intervals
--To take aeroplane utilisation into consideration, in accordance with the A310 life extension programme.
For the reasons stated above, this EASA AD takes over the requirements of paragraph 1.16 of EASA AD 2007-0053R1 [currently at
R3], which has been revised accordingly, and requires accomplishment of the instructions contained in Airbus SB A310-53-2074 at Revision 04.
The unsafe condition is reduced structural integrity of the tail cone.
The required actions include repetitive and one-time inspections, depending on the area, of the lower tail plane cut-out, and corrective actions if necessary. The inspections include the following:
Page 27247
Detailed inspections in areas 1, 2, and 3 for cracking and corrosion of the lower horizontal stabilizer cutout longeron, the corner fitting, the skin strap, and the skin.
Detailed inspections in areas 1, 2, and 3 for damaged sealant.
Eddy current inspections in area 1 for cracking.
Eddy current inspections in area 2 for cracking.
Rotating probe inspection for cracking of specified fastener holes in Area 3.
The corrective actions, depending on the conditions found, include the following:
Repairing corrosion.
Contacting Airbus for repair instructions.
Replacing damaged sealant.
Removing cracking.
Doing an eddy current inspection for cracking of the reworked area.
Installing a new corner fitting.
Doing a rotating probe inspection for cracking of fastener holes.
Doing an eddy current inspection of the longeron and outer skin.
Drilling or reaming fastener holes.
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 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 our FAA policies. Any such differences are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 44 products of U.S. registry.
We also estimate that it will take about 36 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $134,640, or $3,060 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
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 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] 0 2. The FAA amends Sec. 39.13 by adding the following new AD: 2011-10-05 Airbus: Amendment 39-16686. Docket No. FAA-2010-1273;
Directorate Identifier 2010-NM-089-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 15, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model A310-203, -204, -222, -304, -322, and -324 airplanes, certificated in any category, all serial numbers, except airplanes on which Airbus modification 06146 has been done in production.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:
A specific area, the lower tail plane cut-out located in the tail cone is subject to an inspection programme [for cracking] * *
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail cone.
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.
Initial Inspections of the Lower Tail Plane Cut-out Area and Corrective
Actions
(g) Within the applicable time specified in Table 1 of this AD, do the inspections of the lower tail plane cut-out area in the tail cone specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and (g)(6) of this AD, as applicable, in accordance with the
Accomplishment Instructions of Airbus
Page 27248
Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008. Certain compliance times are applicable to short-range use
(i.e., average flight time (AFT) equal to or less than 4 flight hours), or long-range use (i.e., AFT exceeding 4 flight hours).
Inspection areas are specified in Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
Note 1: To establish the average flight time, take the accumulated flight time (counted from the take-off up to the landing) and divide by the number of accumulated flight cycles. This gives the average flight time per flight cycle.
Table 1--Initial Compliance Time
Airplanes
Inspection areas........
Compliance time (whichever occurs later)
Model A310-203, A310-204, and A310- 1 and 2................. Prior to the
Within 1,500 flight 222 airplanes.
accumulation of 18,000 cycles or 3,000 flight total flight cycles or hours, whichever 36,000 total flight
occurs first, after hours, whichever
the effective date of occurs first.
this AD.
Model A310-203, A310-204, and A310- 3....................... Prior to the
Within 1,500 flight 222 airplanes.
accumulation of 24,000 cycles or 3,000 flight total flight cycles or hours, whichever 48,000 total flight
occurs first, after hours, whichever
the effective date of occurs first.
this AD.
Model A310-304, A310-322, and A310- 1 and 2................. Prior to the
Within 1,200 flight 324 short range airplanes.
accumulation of 12,000 cycles or 3,300 flight total flight cycles or hours, whichever 33,750 total flight
occurs first, after hours, whichever
the effective date of occurs first.
this AD.
Model A310-304, A310-322, and A310- 3....................... Prior to the
Within 1,200 flight 324 short range airplanes.
accumulation of 18,000 cycles or 3,300 flight total flight cycles or hours, whichever 50,500 total flight
occurs first, after hours, whichever
the effective date of occurs first.
this AD.
Model A310-304, A310-322, and A310- 1 and 2................. Prior to the
Within 750 flight 324 long range airplanes.
accumulation of 7,500 cycles or 3,750 flight total flight cycles or hours, whichever 37,500 total flight
occurs first, after hours, whichever
the effective date of occurs first.
this AD.
Model A310-304, A310-322, and A310- 3....................... Prior to the
Within 750 flight 324 long range airplanes.
accumulation of 11,250 cycles or 3,750 flight total flight cycles or hours, whichever 56,000 total flight
occurs first, after hours, whichever
the effective date of occurs first.
this AD.
(1) For areas 1, 2, and 3: Do a detailed inspection for cracking and corrosion of the lower horizontal stabilizer cutout longeron, the corner fitting, the skin strap, and the skin, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(i) If any corrosion is found, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(ii) If any cracking is found, before further flight, contact
Airbus for repair instructions and do the repair.
(2) For areas 1, 2, and 3 on which cracking is not found during the inspection required by paragraph (g)(1) of this AD: Do a detailed inspection for damaged sealant; and, if any damaged sealant is found, before further flight, replace the sealant; in accordance with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A310-53-2074, Revision 04, dated October 24, 2008.
(3) For area 1: Do an eddy current inspection for cracking in area 1; and, if no cracking is found, before further flight, apply sealant and corrosion compound, as applicable; in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(i) If cracking is equal to or less than 2.0 mm (0.079 inch) long and not more than 2 cracks with a minimum distance of 50.0 mm
(1.969 inch) between the cracks: Before further flight, remove any cracking and do an eddy current inspection for cracking of the reworked area, in accordance with the Accomplishment Instructions of the Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008. If no cracking is found, before further flight, shot peen the reworked area, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(A) If cracking is found and the radius of the rework is less than 20.0 mm (0.787 inch), before further flight, increase the radius and do an eddy current inspection for cracking of the reworked area, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated
October 24, 2008. If no cracking is found, before further flight, shot peen the reworked area, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008.
(1) If any cracking is found in the outer skin, before further flight, contact Airbus for repair instructions and do the repair.
(2) If any cracking is found in the corner fitting and area 3 has not been cold expanded, before further flight, install new corner fitting, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008, and do the rotating probe inspection in area 3 specified in paragraph (g)(5) of this AD.
(3) If any cracking is found in the corner fitting and area 3 has been cold expanded, before further flight, do the eddy current inspection of the longeron and outer skin specified in paragraph
(g)(6) of this AD.
(B) If cracking is found and the radius of the rework is 20.0 mm
(0.787 inch) or more, before further flight, repair in accordance with a method approved by either the Manager, International Branch,
ANM-116, FAA, Transport Airplane Directorate, or the European
Aviation Safety Agency (EASA) (or its delegated agent)
(ii) If cracking is greater than 2.0 mm (0.079 inch) long or there are more than 2 cracks; or if there are more than 2 cracks with less than a minimum distance of 50.0 mm (1.969 inch) between the cracks: Before further flight, remove the corner fitting, and do the applicable actions specified in paragraph (g)(3)(ii)(A) or
(g)(3)(ii)(B) of this AD.
(A) If any cracking is found and area 3 has not been cold expanded, before further flight, install a new corner fitting, in accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008; and do the rotating probe inspection in area 3 specified in paragraph (g)(5) of this AD.
(B) If any cracking is found and area 3 has been cold expanded, before further flight, do the eddy current inspection of the longeron and outer skin specified in paragraph (g)(6) of this AD.
(4) For area 2: Do an eddy current inspection for cracking of area 2, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310-53-2074, Revision 04, dated October 24, 2008. If any cracking is found, before further flight, contact
Airbus for repair instructions and do the repair.
(5) For area 3: Do a rotating probe inspection for cracking of specified fastener holes in area 3, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(i) If no cracking is found, before further flight, drill or ream fastener holes, cold expand the fastener holes and countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008; except where this service bulletin specifies to contact Airbus if the fastener diameter does not meet specifications or if the distance
Page 27249
between the hole center and material edge is less than specifications, before further flight, contact Airbus for repair instructions and do the repair.
(ii) If cracking is found, before further flight, drill or ream fastener holes, and do a rotating probe inspection for cracking of the fastener holes in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008.
(A) If no cracking is found, cold expand the fastener holes and countersinks, drill or ream fastener holes, and wet install with sealant, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310-53-2074, Revision 04, dated
October 24, 2008; except where this service bulletin specifies to contact Airbus if the fastener diameter does not meet specifications or if the distance between the hole center and material edge is less than the specifications, before further flight, contact Airbus for repair instructions and do the repair.
(B) If cracking is found, before further flight, contact Airbus for repair instructions and do the repair.
(6) For airplanes on which cracking is found in the corner fitting during any inspection required by paragraph (g)(3) of this
AD and area 3 is cold-expanded: Do an eddy current inspection for cracking of the longeron and outer skin, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(i) If no cracking is found, before further flight, install a new corner fitting and do a rotating probe inspection for cracking of the fastener holes, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008.
(A) If no cracking is found, before further flight, drill or ream fastener holes, cold expand the fastener holes and countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(B) If cracking is found and the hole diameter is less than the maximum oversize specification, before further flight, drill or ream holes and do a rotating probe inspection for cracking of the fastener holes, in accordance with Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(1) If no cracking is found, cold expand the fastener holes and countersinks, and wet install with sealant, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2074, Revision 04, dated October 24, 2008.
(2) If cracking is found, before further flight, contact Airbus for repair instructions and do the repair.
(C) If cracking is found and the hole diameter is equal to or greater than the maximum oversize specification, before further flight, contact Airbus for repair instructions and do the repair.
(ii) If cracking is found, before further flight, contact Airbus for repair instructions and do the repair.
Repetitive Inspections of the Lower Tail Plane Cut-Out Area
(h) Repeat the inspections for area 1 required by paragraphs
(g)(1) and (g)(3) of this AD thereafter at the applicable intervals specified in Table 2 of this AD. Certain compliance times are applicable to short-range use (AFT equal to or less than 4 flight hours), or long-range use (AFT exceeding 4 flight hours). Inspection areas are specified in Airbus Mandatory Service Bulletin A310-53- 2074, Revision 04, dated October 24, 2008.
Table 2--Repetitive Interval for Areas 1 and 2
Affected airplanes
Interval (not to exceed)
(1) Model A310-203, A310-204, and A310- 6,000 flight cycles or 12,000 222 airplanes that have accumulated
flight hours, whichever occurs less than 30,000 total flight cycles
first, until the airplane and 60,000 total flight hours, as of
accumulates 30,000 total the effective date of this AD.
flight cycles or 60,000 total flight hours; then perform the inspections within the interval specified in paragraph (h)(2) of this AD.
(2) Model A310-203, A310-204, and A310- 3,900 flight cycles or 7,800 222 airplanes that have accumulated
flight hours, whichever occurs 30,000 total flight cycles or more or first. 60,000 total flight hours or more, as of the effective date of this AD.
(3) Model A310-304, A310-322 and A310- 4,800 flight cycles or 13,500 324 short range airplanes that have
flight hours, whichever occurs accumulated less than 24,000 total
first, until the airplane flight cycles and 67,500 total flight accumulates 24,000 total hours, as of the effective date of
flight cycles or 67,500 total this AD.
flight hours; then perform the inspections within the interval specified in paragraph (h)(4) of this AD.
(4) Model A310-304, A310-322 and A310- 3,100 flight cycles or 8,750 324 short range airplanes that have
flight hours, whichever occurs accumulated 24,000 total flight cycles first. or more or 67,500 total flight hours or more, as of the effective date of this AD.
(5) Model A310-304, A310-322 and A310- 3,000 flight cycles or 15,000 324 long range airplanes that have
flight hours, whichever occurs accumulated less than 15,000 total
first, until the airplane flight cycles and 75,000 total flight accumulates 15,000 total hours, as of the effective date of
flight cycles or 75,000 total this AD.
flight hours; then perform the inspections within the interval specified in paragraph (h)(6) of this AD.
(6) Model A310-304, A310-322 and A310- 1,950 flight cycles or 9,750 324 long range airplanes that have
flight hours, whichever occurs accumulated 15,000 total flight cycles first. or more or 75,000 total flight hours or more, as of the effective date of this AD.
(i) Repeat the inspections for area 2 required by paragraphs
(g)(1) and (g)(4) of this AD thereafter at the applicable intervals specified in Table 2 of this AD. Certain compliance times are applicable to short-range use (AFT equal to or less than 4 flight hours), or long-range use (AFT exceeding 4 flight hours). Inspection areas are specified in Airbus Mandatory Service Bulletin A310-53- 2074, Revision 04, dated October 24, 2008.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(j) Inspections accomplished before the effective date of this
AD in accordance with Airbus Mandatory Service Bulletin A310-53- 2074, Revision 03, dated October 13, 2006, are considered acceptable for compliance with the corresponding action specified in this AD.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information as follows: The MCAI and service information do not specify a corrective action if cracking is found and the radius of the rework is 20.0 mm (0.787 inch) or more. Paragraph (g)(3)(i)(B) of this AD requires repair in accordance with a method approved by either the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate, or EASA (or its delegated agent).
Other FAA AD Provisions
(k) 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. 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
Page 27250
to the International Branch, send it to Attn: Dan Rodina, Aerospace
Engineer, International Branch, ANM-116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057- 3356; telephone (425) 227-2125; fax (425) 227-1149. Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.
Related Information
(l) Refer to MCAI EASA Airworthiness Directive 2009-0058, dated
March 13, 2009; and Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008; for related information.
Material Incorporated by Reference
(m) You must use Airbus Mandatory Service Bulletin A310-53-2074,
Revision 04, dated October 24, 2008, 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 this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail account.airworth-eas@airbus.com;
Internet http://www.airbus.com.
(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 April 22, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
FR Doc. 2011-10688 Filed 5-10-11; 8:45 am
BILLING CODE 4910-13-P
