[Federal Register: January 2, 2008 (Volume 73, Number 1)]
[Proposed Rules]
[Page 80-84]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02ja08-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0372; Directorate Identifier 2007-NM-164-AD]
RIN 2120-AA64
Airworthiness Directives; Construcciones Aeronauticas, S.A.,
(CASA) Model C-212 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:
On 23 November 2006, Emergency Airworthiness Directive (EAD) Nr.
(number) 2006-0351-E was published requiring an inspection to be
performed on C-212 aeroplanes having been used for Maritime Patrol
or other similar low altitude operations, due to the fact that,
after initial examination of the evidences of a recent C-212
Maritime Patrol aircraft accident, cracks had been found in the
centre wing lower skin at STA Y=1030. At the time of the accident,
the aircraft had accumulated 17,000 flight hours and 7,300 flight
cycles. The cracks were suspected to be caused by fatigue.
A more detailed examination in the laboratory, led to think that
the initiation of the fatigue cracks was produced by fretting, and
EAD 2006-0365-E, superseding EAD
[[Page 81]]
2006-0351-E, was published on 4 December 2006 to address the new
situation.
Further examination in the laboratory has allowed to establish
that crack initiation was due to fatigue and the fretting was
posterior.
The above mentioned cracks, if not timely detected, could lead
to reduced structural integrity of the aircraft.
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 February 1,
2008.
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.
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: Shahram Daneshmandi, Aerospace
Engineer, International Branch, ANM-116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, Washington 98057-3356;
telephone (425) 227-1112; 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-2007-0372;
Directorate Identifier 2007-NM-164-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 February 16, 2007, we issued AD 2007-05-01, Amendment 39-14962
(72 FR 8610, February 27, 2007). That AD required actions intended to
address an unsafe condition on the products listed above.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Emergency Airworthiness Directive (EAD) 2007-0108-E, dated April 18,
2007 (referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
On 23 November 2006, Emergency Airworthiness Directive Nr.
(number) 2006-0351-E was published, requiring an inspection to be
performed on C-212 aeroplanes having been used for Maritime Patrol
or other similar low altitude operations, due to the fact that,
after initial examination of the evidences of a recent C-212
Maritime Patrol aircraft accident, cracks had been found in the
centre wing lower skin at STA Y=1030. At the time of the accident,
the aircraft had accumulated 17,000 flight hours and 7,300 flight
cycles. The cracks were suspected to be caused by fatigue.
A more detailed examination in the laboratory, led to think that
the initiation of the fatigue cracks was produced by fretting, and
EAD 2006-0365-E, superseding EAD 2006-0351-E, was published on 4
December 2006 to address the new situation.
Further examination in the laboratory has allowed to establish
that crack initiation was due to fatigue and the fretting was
posterior. Additionally, given that some operators were reporting
difficulties in performing the required inspections, a new procedure
has been defined using High Frequency Eddy Currents. Finally, an
inspection interval has been established to make the required
inspections repetitive in the interim until a definitive solution is
available.
The subject element is identified in Ref. 1 (CASA C-212
Supplemental Inspection Document (SID) C-212-PV-02-SID) as a
Principal Structural Element (PSE) with No. 57.212.06 and requested
to be inspected at a threshold of 20,000 landings (subject to some
operational constraints defined in Ref. 1) in accordance with the
inspection method and sequence described in Ref. 2 (CASA C-212
Supplemental Inspection Procedures (SIP) C-212-PV-02-SIP), Section
57-10-03.
Ref. 1 document was made mandatory by DGAC-Spain Airworthiness
directive Nr. 02/88 (current status of that AD is revision 3, dated
4 February 2004).
Inspection threshold as per AD 02/88 Rev. 3 remains valid and
relevant inspections have to be performed in addition to the
requirements of this Emergency Airworthiness Directive (EAD).
The above mentioned cracks, if not timely detected, could lead
to reduced structural integrity of the aircraft. This EAD [which
supersedes EASA EAD 2006-0365-E], is intended to ensure that no
other C-212 aircraft could be affected by this problem, by mandating
a one time inspection of the subject area and a repetitive
inspection thereafter, until the moment a definitive design solution
will be available, in accordance with the requirements under the
paragraph ``Compliance'' of this EAD.
An additional inspection procedure, by using High Frequency Eddy
Currents, has been introduced, which should be able to detect cracks
with higher reliability.
The corrective action includes repetitive inspections for cracks, and
repair if necessary.
We clarified the compliance times specified in paragraphs (f)(1)(i)
and (f)(2)(i) of the existing AD to specify those times in terms of a
threshold (e.g., 5,600 total flight hours, 2,400 total landings) and a
grace period (e.g., within 6 months), whichever is latest. You may
obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
EADS-CASA has issued All Operator Letter 212-018, Revision 2, dated
March 20, 2007. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
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
[[Page 82]]
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 33 products of U.S. registry. We also estimate that
it would take about 8 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $21,120, or $640 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, 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 39-14962 (72 FR
8610, February 27, 2007) and adding the following new AD:
Construcciones Aeronauticas, S.A. (CASA): Docket No. FAA-2007-0372;
Directorate Identifier 2007-NM-164-AD.
Comments Due Date
(a) We must receive comments by February 1, 2008.
Affected ADs
(b) The proposed AD supersedes AD 2007-05-01, Amendment 39-
14962.
Applicability
(c) This AD applies to Construcciones Aeronauticas, S.A., (CASA)
Model C-212 airplanes; all series, 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:
On 23 November 2006, Emergency Airworthiness Directive Nr.
(number) 2006-0351-E was published, requiring an inspection to be
performed on C-212 aeroplanes having been used for Maritime Patrol
or other similar low altitude operations, due to the fact that,
after initial examination of the evidences of a recent C-212
Maritime Patrol aircraft accident, cracks had been found in the
centre wing lower skin at STA Y=1030. At the time of the accident,
the aircraft had accumulated 17,000 flight hours and 7,300 flight
cycles. The cracks were suspected to be caused by fatigue.
A more detailed examination in the laboratory, led to think that
the initiation of the fatigue cracks was produced by fretting, and
EAD 2006-0365-E, superseding EAD 2006-0351-E, was published on 4
December 2006 to address the new situation.
Further examination in the laboratory has allowed to establish
that crack initiation was due to fatigue and the fretting was
posterior. Additionally, given that some operators were reporting
difficulties in performing the required inspections, a new procedure
has been defined using High Frequency Eddy Currents. Finally, an
inspection interval has been established to make the required
inspections repetitive in the interim until a definitive solution is
available.
The subject element is identified in Ref. 1 (CASA C-212
Supplemental Inspection Document (SID) C-212-PV-02-SID) as a
Principal Structural Element (PSE) with No. 57.212.06 and requested
to be inspected at a threshold of 20,000 landings (subject to some
operational constraints defined in Ref. 1) in accordance with the
inspection method and sequence described in Ref. 2 (CASA C-212
Supplemental Inspection Procedures (SIP) C-212-PV-02-SIP), Section
57-10-03.
Ref. 1 document was made mandatory by DGAC-Spain Airworthiness
directive Nr. 02/88 (current status of that AD is revision 3, dated
4 February 2004).
Inspection threshold as per AD 02/88 Rev. 3 remains valid and
relevant inspections have to be performed in addition to the
requirements of this Emergency Airworthiness Directive (EAD).
The above mentioned cracks, if not timely detected, could lead
to reduced structural integrity of the aircraft. This EAD [which
supersedes EASA EAD 2006-0365-E], is intended to ensure that no
other C-212 aircraft could be affected by this problem, by mandating
a one time inspection of the subject area and a repetitive
inspection thereafter, until the moment a definitive design solution
will be available, in accordance with the requirements under the
paragraph ``Compliance'' of this EAD.
An additional inspection procedure, by using High Frequency Eddy
Currents, has been introduced, which should be able to detect cracks
with higher reliability.
The corrective action includes repetitive inspections for cracks,
and repair if necessary.
Restatement of Requirements of AD 2007-05-01:
(f) Unless already done, do the following actions.
(1) For airplanes used for maritime operations and all other
airplanes on which the operator cannot positively determine that the
airplanes have not been flown more than ten percent of flights at
altitudes below 3,000 feet as of March 14, 2007 (the effective date
of AD 2007-05-01): Perform a Non-Destructive Inspection (NDI) and a
complementary NDI for cracks at the applicable time specified in
paragraph (f)(1)(i), (f)(1)(ii), or (f)(1)(iii) of this AD. Do the
inspections as defined in EADS-CASA All Operator Letter 212-018,
Revision 1, dated December 1, 2006; or Revision 2, dated March 20,
2007. As of the effective date of this AD, only Revision 2 may be
used. -
Note 1: For the purposes of this AD, the term ``maritime
operations'' is defined as airplanes which are used for monitoring
certain areas of water.
[[Page 83]]
(i) For airplanes having accumulated 5,600 flight hours or less,
and 2,400 landings or less as of March 14, 2007: Perform the
inspections before the accumulation of 5,600 total flight hours, or
before the accumulation of 2,400 total landings, or within 6 months
after March 14, 2007, whichever occurs latest.
(ii) For airplanes having accumulated more than 5,600 flight
hours but less than or equal to 8,000 flight hours, or more than
2,400 landings but less than or equal to 3,600 landings, as of March
14, 2007: Perform the inspections before the accumulation of 200
flight hours or 100 landings after March 14, 2007, whichever occurs
first.
(iii) For airplanes having accumulated more than 8,000 flight
hours or more than 3,600 landings as of March 14, 2007: Perform the
inspections within 14 days after March 14, 2007.
(2) For airplanes other than those identified in paragraph
(f)(1) of this AD: Perform the NDIs at the applicable time specified
in paragraph (f)(2)(i), (f)(2)(ii), or (f)(2)(iii) of this AD. Do
the inspections as defined in EADS-CASA All Operator Letter 212-018,
Revision 1, dated December 1, 2006; or Revision 2, dated March 20,
2007. As of the effective date of this AD, only Revision 2 may be
used.
(i) For airplanes having accumulated 10,000 total flight hours
or less, and 10,000 total landings or less as of March 14, 2007:
Perform the inspections before the accumulation of 10,000 total
flight hours, or before the accumulation of 10,000 total landings,
or within 6 months after March 14, 2007, whichever occurs latest.
(ii) For airplanes having accumulated more than 10,000 flight
hours but less than or equal to 15,000 flight hours, or more than
10,000 landings but less than or equal to 15,000 landings, as of
March 14, 2007: Perform the inspections before the accumulation of
200 flight hours or 100 landings after March 14, 2007, whichever
occurs first.
(iii) For airplanes having accumulated more than 15,000 flight
hours or more than 15,000 landings as of March 14, 2007: Perform the
inspections within 14 days after March 14, 2007.
New Requirements of This AD: Actions and Compliance
(g) Unless already done, do the following actions.
(1) For airplanes identified in paragraph (f)(1) of this AD that
have accumulated 5,600 flight hours or less, and 2,400 landings or
less as of the effective date of this AD: Perform the inspections at
the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this
AD. Do the inspections as defined in EADS-CASA All Operator Letter
212-018, Revision 2, dated March 20, 2007.
(i) At the later of the times specified in paragraphs
(g)(1)(i)(A) and (g)(1)(i)(B) of this AD: Perform a high frequency
eddy current (HFEC) NDI for cracks.
(A) Within 200 flight hours or 100 landings after the effective
date of this AD, whichever occurs first.
(B) Before the accumulation of 5,600 total flight hours or 2,400
total landings, whichever occurs first.
(ii) Repeat the inspections required by paragraphs (f)(1) and
(g)(1)(i) of this AD before the accumulation of 8,000 total flight
hours or 3,600 total landings, whichever occurs first, and
thereafter at intervals not to exceed 600 flight hours or 250
landings, whichever occurs first.
(2) For airplanes identified in paragraph (f)(1) of this AD that
have accumulated more than 5,600 flight hours but less than or equal
to 8,000 flight hours, or more than 2,400 landings but less than or
equal to 3,600 landings, as of the effective date of this AD:
Perform the inspections at the times specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD. Do the inspections as defined
in EADS-CASA All Operator Letter 212-018, Revision 2, dated March
20, 2007.
(i) Within 200 flight hours or 100 landings after the effective
date of this AD, whichever occurs first: Perform a HFEC NDI for
cracks.
(ii) Within 600 flight hours or 250 landings, whichever occurs
first, after doing the inspection required by paragraph (g)(2)(i) of
this AD: Perform the inspections required by paragraphs (f)(1) and
(g)(2)(i) of this AD and repeat the inspections thereafter at
intervals not to exceed 600 flight hours or 250 landings, whichever
occurs first.
(3) For airplanes identified in paragraph (f)(1) of this AD that
are not subject to paragraph (g)(1) or (g)(2) of this AD: Perform
the inspections at the times specified in paragraphs (g)(3)(i) and
(g)(3)(ii) of this AD. Do the inspections as defined in EADS-CASA
All Operator Letter 212-018, Revision 2, dated March 20, 2007.
(i) Within 14 days after the effective date of this AD: Perform
a HFEC NDI for cracks.
(ii) Within 600 flight hours or 250 landings, whichever occurs
first, after doing the inspection required by paragraph (g)(3)(i) of
this AD: Perform the inspections required by paragraphs (f)(1) and
(g)(3)(i) of this AD and repeat the inspections thereafter at
intervals not to exceed 600 flight hours or 250 landings, whichever
occurs first.
(4) For airplanes identified in paragraph (f)(2) of this AD that
have accumulated 10,000 flight hours or less, and 10,000 landings or
less, as of the effective date of this AD: Perform the inspections
at the times specified in paragraphs (g)(4)(i) and (g)(4)(ii) of
this AD. Do the inspections as defined in EADS-CASA All Operator
Letter 212-018, Revision 2, dated March 20, 2007.
(i) Within 200 flight hours or 100 landings after the effective
date of this AD, whichever occurs first: Perform a HFEC NDI for
cracks.
(ii) Repeat the inspections required by paragraphs (f)(2) and
(g)(4)(i) of this AD before the accumulation of 15,000 total flight
hours or 15,000 total landings, whichever occurs first, and
thereafter at intervals not to exceed 4,500 flight hours or 4,500
landings, whichever occurs first.
(5) For airplanes identified in paragraph (f)(2) of this AD that
have accumulated more than 10,000 flight hours but less than or
equal to 15,000 flight hours, or more than 10,000 landings but less
than or equal to 15,000 landings, as of the effective date of this
AD: Perform the inspections at the time specified in paragraphs
(g)(5)(i) and (g)(5)(ii) of this AD. Do the inspections as defined
in EADS-CASA All Operator Letter 212-018, Revision 2, dated March
20, 2007.
(i) Within 200 flight hours or 100 landings after the effective
date of this AD, whichever occurs first: Perform a HFEC NDI for
cracks.
(ii) Within 4,500 flight hours or 4,500 landings, whichever
occurs first, after doing the inspection required by paragraph
(g)(5)(i) of this AD: Perform the inspections required by paragraphs
(f)(2) and (g)(5)(i) of this AD. Repeat the inspections thereafter
at intervals not to exceed 4,500 flight hours or 4,500 landings,
whichever occurs first.
(6) For airplanes identified in paragraph (f)(2) of this AD that
are not subject to paragraph (g)(4) or (g)(5) of this AD: Perform
the inspections at the time specified in paragraphs (g)(6)(i) and
(g)(6)(ii) of this AD. Do the inspections as defined in EADS-CASA
All Operator Letter 212-018, Revision 2, dated March 20, 2007.
(i) Within 14 days after the effective date of this AD: Perform
a HFEC NDI for cracks.
(ii) Within 4,500 flight hours or 4,500 landings, whichever
occurs first, after doing the inspection required by paragraph
(g)(6)(i) of this AD: Perform the inspections required by paragraphs
(f)(2) and (g)(6)(i) of this AD, and repeat the inspection
thereafter at intervals not to exceed 4,500 flight hours or 4,500
landings, whichever occurs first.
(7) If any crack or loose rivet is detected during any
inspection required by this AD, before further flight, repair using
a method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation
Safety Agency (EASA) (or its delegated agent). Within 30 days after
cracks are detected, or within 30 days after the effective date of
this AD, whichever occurs later, send a detailed report of the first
inspection findings (both positive and negative) of the inspections
required by paragraph (f) of this AD to EADS-CASA for evaluation at
the following address: EADS-CASA, Military Transport Aircraft
Division, Integrated Customer Services, Technical Services, Avenida
de Aragon 404, 28022-Madrid, Spain; telephone 34-91-624-6306; fax
34-91-585-5505; E-mail: MTA, TechnicalService@casa.eads.net. In any
case, a confirmation of the accomplishment of this inspection is
required to be sent to EADS-CASA.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows:
(1) Compliance Time: For certain airplanes, the compliance time
required by the MCAI or service information for performing the HFEC
inspections is before further flight; however, to avoid
inadvertently grounding airplanes, this AD requires performing those
inspections within 14 days after the effective date of this AD.
(2) Repair: Although the MCAI or service information does not
include a repair procedure for cracking, this AD requires the repair
of any cracking per the FAA or EASA (or its delegated agent).
Other FAA AD Provisions
(h) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International
[[Page 84]]
Branch, ANM-116, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Shahram Daneshmandi, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1112; fax (425) 227-1149. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(i) Refer to MCAI EASA Emergency Airworthiness Directive 2007-
0108-E, dated April 18, 2007, and EADS-CASA All Operator Letter 212-
018, Revision 2, dated March 20, 2007, for related information.
Issued in Renton, Washington, on December 19, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-25481 Filed 12-31-07; 8:45 am]
BILLING CODE 4910-13-P