[Federal Register: March 19, 2008 (Volume 73, Number 54)]
[Rules and Regulations]
[Page 14661-14665]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19mr08-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29030; Directorate Identifier 2006-NM-284-AD;
Amendment 39-15432; AD 2008-06-20]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F.28 Mark 0070, 0100,
1000, 2000, 3000, and 4000 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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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:
Subsequent to accidents involving Fuel Tank System explosions in
flight * * * and on ground, * * * Special Federal Aviation
Regulation 88 (SFAR88) * * * required a safety review of the
aircraft Fuel Tank System * * *.
* * * * *
Fuel Airworthiness Limitations are items arising from a systems
safety analysis that have been shown to have failure mode(s)
associated with an `unsafe condition' * * *. These are identified in
Failure Conditions for which an unacceptable probability of ignition
risk could exist if specific tasks and/or practices are not
performed in accordance with the manufacturers' requirements.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective April 23, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 23,
2008.
ADDRESSES: You may examine the AD docket on the Internet at http://
www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on August 21, 2007 (72
FR 46572). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
Subsequent to accidents involving Fuel Tank System explosions in
flight * * * and on ground, the FAA published Special Federal
Aviation Regulation 88 (SFAR 88) in June 2001. SFAR 88 required a
safety review of the aircraft Fuel Tank System to determine that the
design meets the requirements of FAR (Federal Aviation Regulation)
Sec. 25.901 and Sec. 25.981(a) and (b).
A similar regulation has been recommended by the JAA (Joint
Aviation Authorities) to the European National Aviation Authorities
in JAA letter 04/00/02/07/03-L024 of 3 February 2003. The review was
requested to be mandated by NAA's (National Aviation Authorities)
using JAR (Joint Aviation Regulation) Sec. 25.901(c), Sec.
25.1309.
In August 2005 EASA published a policy statement on the process
for developing instructions for maintenance and inspection of Fuel
Tank System ignition source prevention (EASA D 2005/CPRO, http://
www.easa.eu.int/home/cert_policy_statements_en.html) that also
included the EASA expectations with regard to compliance times of
the corrective actions on the unsafe and the not unsafe part of the
harmonised design review results. On a global scale the TC (type
certificate) holders committed themselves to the EASA published
compliance dates (see EASA policy statement). The EASA policy
statement has been revised in March 2006: the date of 31-12-2005 for
the unsafe related actions has now been set at 01-07-2006.
Fuel Airworthiness Limitations are items arising from a systems
safety analysis that have been shown to have failure mode(s)
associated with an `unsafe condition' as defined in FAA's memo 2003-
112-15 `SFAR 88--Mandatory Action Decision Criteria'. These are
identified in Failure Conditions for which an unacceptable
probability of ignition risk could exist if specific tasks and/or
practices are not performed in accordance with the manufacturers'
requirements.
This EASA Airworthiness Directive mandates the Fuel System
Airworthiness Limitations, comprising maintenance/inspection tasks
and Critical Design Configuration Control Limitations (CDCCL) for
the type of aircraft, that resulted from the design reviews and the
JAA recommendation and EASA policy statement mentioned above.
The corrective action includes revising the Airworthiness Limitations
Section of the Instructions for Continued Airworthiness for certain
airplanes, and
[[Page 14662]]
the FAA-approved maintenance program for certain other airplanes, to
incorporate new limitations for fuel tank systems. You may obtain
further information by examining the MCAI in the AD docket.
Actions Since the NPRM Was Issued
Since we issued the NPRM, we have received Fokker Service Bulletin
SBF28-28-050, Revision 1, dated January 8, 2008. (We referred to Fokker
Service Bulletin F28/28-050, dated June 30, 2006, in the NPRM as an
appropriate source of service information for accomplishing the
required actions.) Revision 1 of the service bulletin includes
editorial changes, changes to certain CDCCL control references, and
changes to the compliance paragraph. We have changed paragraphs (f) and
(h) of the AD to refer to Revision 1 of the service bulletin. We have
also added a new paragraph (f)(5) to the AD to specify, in part, that
actions done before the effective date of this AD in accordance with
Fokker Service Bulletin F28/28-050, dated June 30, 2006, are acceptable
for compliance with the corresponding requirements of this AD.
Operators should note that we have excluded the CDCCL component
titled ``Level Control Pilot Valve Solenoid, jiffy junction,'' from the
requirements of paragraph (f)(2)(i) of this AD. Fokker 70/100 Fuel
Airworthiness Limitation Items (ALI) and Critical Design Configuration
Control Limitations (CDCCL) Report SE-672, Issue 2, specifies that the
appropriate reference for this CDCCL control has not yet been
published. Therefore, we cannot include it in the requirements of this
AD. We may consider additional rulemaking to address this item when the
reference is available.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request To Refer to Later Revision of Report
SAM Airlines requests that we revise paragraph (f) of the AD to
refer to Fokker 70/100 Fuel Airworthiness Limitation Items (ALI) and
Critical Design Configuration Control Limitations (CDCCL) Report SE-
672, Issue 2, dated December 1, 2006. SAM Airlines points out that EASA
AD 2006-0208, dated July 12, 2006 (a parallel EASA Airworthiness
Directive for this AD), includes provisions to use Issue 1 of the
report ``or later approved revisions.'' However, the NPRM does not
allow for use of later approved revisions of this report as an
acceptable means of compliance. SAM Airlines would like to know if the
use of later revisions of the report would require approval through the
provisions of paragraph (g)(1) of the NPRM.
We agree with the commenter's request. In the NPRM, we referred to
Issue 1, dated January 31, 2006, of the report as the appropriate
source of service information for accomplishing the required actions.
Issue 2 of the report includes the CDCCL control references, as
published in the June 1, 2006, revision of the airplane maintenance
manual. Issue 2 also changes task descriptions for the fuel ALIs in
accordance with the Maintenance Review Board document.
We have revised paragraphs (f) and (h) of this AD to refer to Issue
2 of the report. We have also specified in the new paragraph (f)(5) of
the AD that actions done before the effective date of this AD in
accordance with Issue 1 of Report SE-672 are acceptable for compliance
with the corresponding requirements of this AD. We also revised
paragraph (f)(4) of this AD to allow the use of later revisions of the
report, if those revisions are approved by the Manager, International
Branch, ANM-116, FAA, or the European Aviation Safety Agency (EASA), or
its delegated agent.
Request To Remove Reference to Service Information in Certain
Paragraphs
SAM Airlines also requests that we remove the reference to Fokker
Service Bulletin F28/28-050, dated June 30, 2006, from paragraphs
(f)(1)(i) and (f)(2)(i) of the NPRM. SAM Airlines points out that those
paragraphs apply only to Fokker Model F.28 Mark 0070 and 0100
airplanes, which are not included in Fokker Service Bulletin F28/28-
050.
We agree with SAM Airlines for the reason stated. We infer that SAM
Airlines also requests we remove the reference to Fokker 70/100 Fuel
Airworthiness Limitation Items (ALI) and Critical Design Configuration
Control Limitations (CDCCL) Report SE-672, Issue 1, dated January 31,
2006, from paragraphs (f)(1)(ii) and (f)(2)(ii) of the NPRM because
those paragraphs apply only to Fokker Model F.28 Mark 1000, 2000, 3000,
and 4000 airplanes, which are not included in Report SE-672. We have
revised paragraphs (f)(1)(i), (f)(1)(ii), (f)(2)(i), and (f)(2)(ii) of
the AD to refer only to the applicable documents.
Request To Clarify Changes to Maintenance Program
SAM Airlines also requests that we clarify paragraphs (f)(1)(i) and
(f)(2)(i) of the NPRM regarding what changes are being made to the
maintenance program. SAM states that the meaning of the word ``limits''
in paragraph (f)(1)(i) of the NPRM is unclear. In SAM Airlines'
interpretation, the intended action in paragraph (f)(1)(i) is to
incorporate into the aircraft maintenance program the intervals of the
fuel ALI tasks. If so, SAM Airlines requests that we revise the wording
to say: ``* * * Instructions for Continued Airworthiness and
incorporate the Fuel ALI tasks and intervals specified in Fokker * *
*.''
SAM Airlines also explains that accomplishing the CDCCL is
unscheduled and requires distinguishing which inspection is needed in
addition to the normal maintenance task. Therefore, it is not practical
to incorporate the CDCCL into the aircraft maintenance program, as
specified in paragraph (f)(2)(i) of the NPRM. SAM Airlines suggests the
following wording to clarify paragraph (f)(2)(i) of the NPRM: ``* * *
Instructions for Continued Airworthiness and adhere to the CDCCL
requirements as defined in Fokker * * *.''
We agree that clarification is necessary. This AD requires affected
operators to revise their copies of their Airworthiness Limitations
document to incorporate the fuel system limitation inspections. This
consists of the inspections, thresholds, and intervals. We have added
these terms to paragraphs (f)(1)(i) and (f)(1)(ii) of this AD. The AD
also requires revising the Airworthiness Limitations Section (ALS) to
incorporate the CDCCLs as defined in the applicable service
information.
Further, for airplanes that do not have an ALI, this AD requires
that operators revise the maintenance program to include the ALI
inspections, thresholds, and intervals. It also requires incorporation
of the CDCCLs as defined in the applicable service information to
ensure that the specified design configurations are maintained whenever
any work is performed.
Subsequently, section 91.403(c) of the Federal Aviation Regulations
(14 CFR 91.403(c)) requires an affected operator to comply with the
revised Airworthiness Limitations document. Ensuring that one's
maintenance program and the actions of its maintenance personnel are in
accordance with the Airworthiness
[[Page 14663]]
Limitations is required, but not by the AD. According to 14 CFR
91.403(c), no person may operate an aircraft for which airworthiness
limitations have been issued unless those limitations have been
complied with. Therefore, there is no need to further expand the
requirements of the AD beyond that which was proposed because 14 CFR
91.403(c) already imposes the appropriate required action after the
airworthiness limitations are revised.
Explanation of Additional Changes Made to This AD
For standardization purposes, we have revised this AD in the
following ways:
In most ADs, we adopt a compliance time allowing a
specified amount of time after the AD's effective date. In this case,
however, the FAA has already issued regulations that require operators
to revise their maintenance/inspection programs to address fuel tank
safety issues. The compliance date for these regulations is December
16, 2008. To provide for coordinated implementation of these
regulations and this AD, we are including this same compliance date in
paragraphs (f)(1) and (f)(2) of this AD.
We have simplified the language in Note 1 of this AD to
clarify that an operator must request approval for an alternative
method of compliance (AMOC) if an operator cannot accomplish the
required inspections because an airplane has been previously modified,
altered, or repaired in the areas addressed by the required
inspections.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 18 products of U.S. registry.
We also estimate that it will take about 1 work-hour 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 $1,440, or $80 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 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
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 adding the following new AD:
2008-06-20 Fokker Services B.V.: Amendment 39-15432. Docket No. FAA-
2007-29030; Directorate Identifier 2006-NM-284-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
23, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Fokker Model F.28 Mark 0070 and 0100
airplanes, all serial numbers, certificated in any category; and
Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes, serial numbers
11003 through 11241, 11991 and 11992, certificated in any category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (g)(1) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued operational safety of the airplane.
Subject
(d) Transport Association (ATA) of America Code 28: Fuel.
[[Page 14664]]
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Subsequent to accidents involving Fuel Tank System explosions in
flight * * * and on ground, the FAA published Special Federal
Aviation Regulation 88 (SFAR 88) in June 2001. SFAR 88 required a
safety review of the aircraft Fuel Tank System to determine that the
design meets the requirements of FAR (Federal Aviation Regulation)
Sec. 25.901 and Sec. 25.981(a) and (b).
A similar regulation has been recommended by the JAA (Joint
Aviation Authorities) to the European National Aviation Authorities
in JAA letter 04/00/02/07/03-L024 of 3 February 2003. The review was
requested to be mandated by NAA's (National Aviation Authorities)
using JAR (Joint Aviation Regulation) Sec. 25.901(c), Sec.
25.1309.
In August 2005 EASA published a policy statement on the process
for developing instructions for maintenance and inspection of Fuel
Tank System ignition source prevention (EASA D 2005/CPRO, http://
www.easa.eu.int/home/cert_policy_statements_en.html) that also
included the EASA expectations with regard to compliance times of
the corrective actions on the unsafe and the not unsafe part of the
harmonised design review results. On a global scale the TC (type
certificate) holders committed themselves to the EASA published
compliance dates (see EASA policy statement). The EASA policy
statement has been revised in March 2006: The date of 31-12-2005 for
the unsafe related actions has now been set at 01-07-2006.
Fuel Airworthiness Limitations are items arising from a systems
safety analysis that have been shown to have failure mode(s)
associated with an `unsafe condition' as defined in FAA's memo 2003-
112-15 `SFAR 88--Mandatory Action Decision Criteria'. These are
identified in Failure Conditions for which an unacceptable
probability of ignition risk could exist if specific tasks and/or
practices are not performed in accordance with the manufacturers'
requirements.
This EASA Airworthiness Directive mandates the Fuel System
Airworthiness Limitations, comprising maintenance/inspection tasks
and Critical Design Configuration Control Limitations (CDCCL) for
the type of aircraft, that resulted from the design reviews and the
JAA recommendation and EASA policy statement mentioned above.
The corrective action includes revising the Airworthiness
Limitations Section of the Instructions for Continued Airworthiness
for certain airplanes, and the FAA-approved maintenance program for
certain other airplanes, to incorporate new limitations for fuel
tank systems.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 3 months after the effective date of this AD or
before December 16, 2008, whichever occurs first, do the action in
paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as applicable. For all
identified tasks, the initial compliance time starts from the
effective date of this AD. The repetitive inspections must be
accomplished thereafter at the intervals not to exceed those
specified in Fokker 70/100 Fuel Airworthiness Limitation Items (ALI)
and Critical Design Configuration Control Limitations (CDCCL) Report
SE-672, Issue 2, dated December 1, 2006; or Fokker Service Bulletin
SBF28-28-050, Revision 1, dated January 8, 2008; as applicable;
except as provided by paragraphs (f)(3), (f)(4), and (g)(1) of this
AD.
(i) For Model F.28 Mark 0070 and 0100 airplanes: Revise the
Airworthiness Limitations Section (ALS) of the Instructions for
Continued Airworthiness to incorporate the inspections, thresholds,
and intervals specified in Fokker 70/100 Fuel Airworthiness
Limitation Items (ALI) and Critical Design Configuration Control
Limitations (CDCCL) Report SE-672, Issue 2, dated December 1, 2006.
(ii) For Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes:
Incorporate into the FAA-approved maintenance inspection program the
inspections, thresholds, and intervals specified in Fokker Service
Bulletin SBF28-28-050, Revision 1, dated January 8, 2008.
(2) Within 3 months after the effective date of this AD or
before December 16, 2008, whichever occurs first, do the action in
paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as applicable.
(i) For Model F.28 Mark 0070 and 0100 airplanes: Revise the
Airworthiness Limitations Section (ALS) of the Instructions for
Continued Airworthiness to incorporate the CDCCLs as defined in
Fokker 70/100 Fuel Airworthiness Limitation Items (ALI) and Critical
Design Configuration Control Limitations (CDCCL) Report SE-672,
Issue 2, dated December 1, 2006, except for the CDCCL component
titled ``Level Control Pilot Valve Solenoid, jiffy junction.''
(ii) For Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes:
Incorporate into the FAA-approved maintenance inspection program the
CDCCLs as defined in Fokker Service Bulletin SBF28-28-050, Revision
1, dated January 8, 2008.
(3) Where Fokker 70/100 Fuel Airworthiness Limitation Items
(ALI) and Critical Design Configuration Control Limitations (CDCCL)
Report SE-672, Issue 2, dated December 1, 2006; and Fokker Service
Bulletin SBF28-28-050, Revision 1, dated January 8, 2008; allow for
exceptional short-term extensions, an exception is acceptable to the
FAA if it is approved by the appropriate principal inspector in the
FAA Flight Standards Certificate Holding District Office.
(4) After accomplishing the actions specified in paragraphs
(f)(1) and (f)(2) of this AD, no alternative inspection, inspection
interval, or CDCCL may be used, unless the inspection, interval, or
CDCCL is part of a later revision of Fokker 70/100 Fuel
Airworthiness Limitation Items (ALI) and Critical Design
Configuration Control Limitations (CDCCL) Report SE-672, Issue 2,
dated December 1, 2006; or Fokker Service Bulletin SBF28-28-050,
Revision 1, dated January 8, 2008; as applicable; that is approved
by the Manager, ANM-116, International Branch, Transport Airplane
Directorate, FAA, or the European Aviation Safety Agency (EASA), or
its delegated agent, or unless the inspection, interval, or CDCCL is
approved as an alternative method of compliance (AMOC) in accordance
with the procedures specified in paragraph (g)(1) of this AD.
(5) Actions done before the effective date of this AD in
accordance with Fokker 70/100 Fuel Airworthiness Limitation Items
(ALI) and Critical Design Configuration Control Limitations (CDCCL)
Report SE-672, Issue 1, dated January 31, 2006; or Fokker Service
Bulletin F28/28-050, dated June 30, 2006; are acceptable for
compliance with the corresponding requirements of this AD.
Note 2: For Model F.28 Mark 1000, 2000, 3000, and 4000
airplanes, after an operator complies with the requirements of
paragraphs (f)(1)(ii) and (f)(2)(ii) of this AD, those paragraphs do
not require that operators subsequently record accomplishment of
those requirements each time an applicable action is accomplished
according to that operator's FAA-approved maintenance inspection
program.
FAA AD Differences
Note 3: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. Send information to ATTN: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-1137; fax (425) 227-1149. Before using any approved AMOC
on any airplane to which the AMOC applies, notify your 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
(h) Refer to MCAI European Aviation Safety Agency (EASA)
Airworthiness Directive 2006-0206, dated June 11, 2006; EASA
Airworthiness Directive 2006-0208, dated July 12, 2006; Fokker 70/
100 Fuel Airworthiness Limitation Items (ALI) and Critical Design
Configuration Control
[[Page 14665]]
Limitations (CDCCL) Report SE-672, Issue 2, dated December 1, 2006;
and Fokker Service Bulletin SBF28-28-050, Revision 1, dated January
8, 2008; for related information.
Material Incorporated by Reference
(i) You must use Fokker 70/100 Fuel Airworthiness Limitation
Items (ALI) and Critical Design Configuration Control Limitations
(CDCCL) Report SE-672, Issue 2, dated December 1, 2006; and Fokker
Service Bulletin SBF28-28-050, Revision 1, dated January 8, 2008; 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 this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the
Netherlands.
(3) 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: http://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued in Renton, Washington, on March 9, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-5142 Filed 3-18-08; 8:45 am]
BILLING CODE 4910-13-P