Airworthiness Directives; Construcciones Aeronauticas, S.A. (CASA), Model C-212 Airplanes, 13433-13436 [E8-4936]
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13433
Rules and Regulations
Federal Register
Vol. 73, No. 50
Thursday, March 13, 2008
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0372; Directorate
Identifier 2007–NM–164–AD; Amendment
39–15425; AD 2008–06–13]
RIN 2120–AA64
Airworthiness Directives;
Construcciones Aeronauticas, S.A.
(CASA), Model C–212 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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SUMMARY: We are superseding an
existing 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:
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
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.
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The above mentioned cracks, if not timely
detected, could lead to reduced structural
integrity of the aircraft.* * *
*
*
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective April
17, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 17, 2008.
The Director of the Federal Register
approved the incorporation by reference
of EADS–CASA All Operator Letter
212–018, Revision 1, dated December 1,
2006, listed in this AD as of March 14,
2007 (72 FR 8610, February 27, 2007).
ADDRESSES: You may examine the AD
docket on the Internet at https://
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:
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:
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 2, 2008 (73 FR 80),
and proposed to supersede AD 2007–
05–01, Amendment 39–14962 (72 FR
8610, February 27, 2007). That NPRM
proposed to correct an unsafe condition
for the specified products. The MCAI
states:
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,
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Sfmt 4700
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. 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.
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Federal Register / Vol. 73, No. 50 / Thursday, March 13, 2008 / Rules and Regulations
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
about 33 products of U.S. registry. We
also estimate that it will take about 8
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $21,120, or $640 per product.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this 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
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16:22 Mar 12, 2008
Jkt 214001
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 https://
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–14962 (72 FR
8610, February 27, 2007) and adding the
following new AD:
I
2008–06–13 Construcciones Aeronauticas,
S.A. (CASA): Amendment 39–15425.
Docket No. FAA–2007–0372; Directorate
Identifier 2007–NM–164–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 17, 2008.
Affected ADs
(b) This AD supersedes AD 2007–05–01,
Amendment 39–14962.
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Applicability
(c) This AD applies to 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 (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
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
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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 NonDestructive 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.
(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
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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
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13435
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–
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CASA, Military Transport Aircraft Division,
Integrated Customer Services, Technical
Services, Avenida de Aragon 404, 28022Madrid, 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).
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Other FAA AD Provisions
(h) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
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.
Material Incorporated by Reference
(j) You must use EADS–CASA All Operator
Letter 212–018, Revision 1, dated December
1, 2006; and EADS–CASA All Operator Letter
212–018, Revision 2, dated March 20, 2007;
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16:22 Mar 12, 2008
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as applicable; 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
EADS–CASA All Operator Letter 212–018,
Revision 2, dated March 20, 2007, under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of EADS–CASA All Operator Letter
212–018, Revision 1, dated December 1,
2006, on March 14, 2007 (72 FR 8610,
February 27, 2007).
(3) For service information identified in
this AD, contact Construcciones
Aeronauticas, S.A., Getafe, Madrid, Spain.
(4) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March 4,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–4936 Filed 3–12–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0270; Directorate
Identifier 2007–NM–211–AD; Amendment
39–15426; AD 2008–06–14]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757–200, –200PF, and –200CB
Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Boeing Model 757–200, –200PF, and
–200CB series airplanes. This AD
requires doing an ultrasound inspection
for disbonded tear straps not
mechanically fastened to the skin, and
related investigative and corrective
actions, if necessary. This AD results
from reports indicating that bonded skin
panels may not have been correctly
anodized in phosphoric acid before the
tear strap doubler was bonded to the
skin. We are issuing this AD to detect
and correct a weak bond between the
skin and tear strap. Such disbonding
could reduce the ability of the skin to
resist cracks and could adversely affect
the structural integrity of the airplane.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
This AD is effective April 17,
2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 17, 2008.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
DATES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Jason Deutschman, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6449; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to
certain Boeing Model 757–200, –200PF,
and –200CB series airplanes. That
NPRM was published in the Federal
Register on December 17, 2007 (72 FR
71277). That NPRM proposed to require
an ultrasound inspection for disbonded
tear straps not mechanically fastened to
the skin, and related investigative and
corrective actions, if necessary.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the two comments received.
Boeing and Continental Airlines support
the NPRM.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
There are 744 airplanes of the affected
design in the worldwide fleet. This AD
E:\FR\FM\13MRR1.SGM
13MRR1
Agencies
[Federal Register Volume 73, Number 50 (Thursday, March 13, 2008)]
[Rules and Regulations]
[Pages 13433-13436]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-4936]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 73, No. 50 / Thursday, March 13, 2008 / Rules
and Regulations
[[Page 13433]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0372; Directorate Identifier 2007-NM-164-AD;
Amendment 39-15425; AD 2008-06-13]
RIN 2120-AA64
Airworthiness Directives; Construcciones Aeronauticas, S.A.
(CASA), Model C-212 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing 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:
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 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.* * *
* * * * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective April 17, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 17,
2008.
The Director of the Federal Register approved the incorporation by
reference of EADS-CASA All Operator Letter 212-018, Revision 1, dated
December 1, 2006, listed in this AD as of March 14, 2007 (72 FR 8610,
February 27, 2007).
ADDRESSES: You may examine the AD docket on the Internet at https://
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: 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:
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 2, 2008 (73
FR 80), and proposed to supersede AD 2007-05-01, Amendment 39-14962 (72
FR 8610, February 27, 2007). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
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 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. 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.
[[Page 13434]]
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 about 33 products of U.S.
registry. We also estimate that it will take about 8 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Based on these figures, we estimate
the cost of this AD to the 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 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 https://
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
0
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 removing Amendment 39-14962 (72 FR
8610, February 27, 2007) and adding the following new AD:
2008-06-13 Construcciones Aeronauticas, S.A. (CASA): Amendment 39-
15425. Docket No. FAA-2007-0372; Directorate Identifier 2007-NM-164-
AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
17, 2008.
Affected ADs
(b) This AD supersedes AD 2007-05-01, Amendment 39-14962.
Applicability
(c) This AD applies to 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 (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 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
[[Page 13435]]
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.
(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-
[[Page 13436]]
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 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.
Material Incorporated by Reference
(j) You must use EADS-CASA All Operator Letter 212-018, Revision
1, dated December 1, 2006; and EADS-CASA All Operator Letter 212-
018, Revision 2, dated March 20, 2007; as applicable; 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 EADS-CASA All Operator Letter 212-018,
Revision 2, dated March 20, 2007, under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of EADS-CASA All Operator Letter 212-018,
Revision 1, dated December 1, 2006, on March 14, 2007 (72 FR 8610,
February 27, 2007).
(3) For service information identified in this AD, contact
Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain.
(4) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued in Renton, Washington, on March 4, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-4936 Filed 3-12-08; 8:45 am]
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