Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes, 69427-69430 [05-22589]
Download as PDF
<![CDATA[
Federal Register / Vol. 70, No. 220 / Wednesday, November 16, 2005 / Rules and Regulations
69427
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
the FAA amends 14 CFR part 39 as
follows:
2005–23–17 Boeing: Amendment 39–14375.
Docket No. FAA–2004–19539;
Directorate Identifier 2004–NM–06–AD.
PART 39—AIRWORTHINESS
DIRECTIVES
Effective Date
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
I
Adoption of the Amendment
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
Affected ADs
(b) None.
Applicability
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
Accordingly, under the authority
delegated to me by the Administrator,
I
(a) This AD becomes effective December
21, 2005.
(c) This AD applies to the Boeing airplanes
listed in Table 1 of this AD, certificated in
any category:
TABLE 1.—APPLICABILITY
Airplane
Line numbers
Model 737–100, –200, –200C, –300, –400, and –500 series airplanes ...................................................................
Model 737–600, –700, –700C, –800, and –900 series airplanes .............................................................................
Unsafe Condition
(d) This AD was prompted by evidence of
chafed wiring behind the P15 refuel panel
and arcing to the back of the P15 refuel panel
and adjacent wing structure. We are issuing
this AD to detect and correct chafing of the
wiring behind the P15 refuel panel, which
could lead to arcing and fire with consequent
airplane damage and injury to refueling
personnel.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Inspection and Corrective Actions
(f) Within 18 months after the effective
date of this AD, perform the following
actions as applicable:
(1) For Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes: Perform a
one-time detailed inspection of the wires in
wire bundle W0024 to connector D04578P on
the back of the P15 refuel panel for
discrepancies, and do any applicable
corrective and related investigative actions
before further flight, in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–28–
1193, Revision 1, dated July 28, 2005.
(2) For Model 737–600, –700, –700C, –800,
and –900 series airplanes: Perform all
applicable actions listed in paragraphs
(f)(2)(i) and (f)(2)(ii) of this AD in accordance
with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
737–28–1200, Revision 1, dated July 28,
2005.
(i) For Group 1 and Group 2 airplanes as
defined in Service Bulletin 737–28–1200:
Perform a one-time detailed inspection for
discrepancies of the clamp and T-bolt
assembly on the wing thermal anti-ice duct
near the P15 refuel panel and do any
applicable corrective actions before further
flight.
(ii) For Group 2 airplanes only as defined
in Service Bulletin 737–28–1200: Perform a
one-time detailed inspection for
VerDate Aug<31>2005
11:21 Nov 15, 2005
Jkt 208001
1 through 3132 inclusive.
0001 through 1240 inclusive.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive visual
examination of a specific structural area,
system, installation, or assembly to detect
damage, failure, or irregularity. Available
lighting is normally supplemented with a
direct source of good lighting at intensity
deemed appropriate by the inspector.
Inspection aids such as mirror, magnifying
lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be
required.’’
Credit for Actions Done Previously
(g) Actions accomplished before the
effective date of this AD in accordance with
Boeing Special Attention Service Bulletin
737–28–1193, dated April 24, 2003; or
Boeing Special Attention Service Bulletin
737–28–1200, dated July 10, 2003; as
applicable; including Information Notices
737–28–1193 IN 01 and 737–28–1200 IN 01;
both dated September 11, 2003; as
applicable, are acceptable for compliance
with the corresponding actions required by
this AD.
applicable; to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207,
for a copy of this service information. You
may review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., room PL–401, Nassif
Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 7, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–22591 Filed 11–15–05; 8:45 am]
discrepancies of the wires in wire bundle
W0024 to connector D04578P on the back of
the P15 refuel panel and do any applicable
corrective actions before further flight.
BILLING CODE 4910–13–P
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
DEPARTMENT OF TRANSPORTATION
Material Incorporated by Reference
(i) You must use Boeing Special Attention
Service Bulletin 737–28–1193, Revision 1,
dated July 28, 2005; or Boeing Special
Attention Service Bulletin 737–28–1200,
Revision 1, dated July 28, 2005; as
AGENCY:
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22972; Directorate
Identifier 2003–NM–265–AD; Amendment
39–14376; AD 2005–23–18]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F27 Mark 050 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
E:\FR\FM\16NOR1.SGM
16NOR1
69428
Federal Register / Vol. 70, No. 220 / Wednesday, November 16, 2005 / Rules and Regulations
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Fokker Model F27 Mark 050 airplanes.
This AD requires a one-time inspection
of the bleed air supply ducts to
determine if blanking plugs are present
and a one-time inspection of the entire
area of the engine nacelle for heat
damage; and corrective actions if
necessary. This AD also requires
replacement of the blanking plugs with
clamping devices. This AD results from
heat damage in areas adjacent to the
bleed air supply duct assembly. We are
issuing this AD to prevent rupture of the
bleed air supply duct, which could lead
to hot bleed air leaking into the engine
controls area and result in heat damage
to control cables, electrical wiring,
hydraulic components, and fuel lines,
and consequent fire.
DATES: This AD becomes effective
December 1, 2005.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of December 1, 2005.
We must receive comments on this
AD by January 17, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Fokker Services B.V., P.O.
Box 231, 2150 AE Nieuw-Vennep, the
Netherlands, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1137;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority—The
Netherlands (CAA–NL), which is the
airworthiness authority for the
Netherlands, notified us that an unsafe
VerDate Aug<31>2005
11:21 Nov 15, 2005
Jkt 208001
condition may exist on all Fokker Model
F27 Mark 050 airplanes. The CAA–NL
advises that an operator found heat
damage in areas adjacent to the bleed air
supply duct assembly while inspecting
for hydraulic leakage in the engine
controls area on a Model F27 Mark 050
airplane. The same operator also found
a second airplane with heat damage
after inspecting its remaining fleet.
Further investigation revealed that the
inner wall of the bleed air supply duct
was ruptured, which caused bleed air to
escape and blow out the three blanking
plugs that are fitted on the outer wall of
the bleed air supply duct. As a result,
hot bleed air vented into the engine
controls area through the holes in the
outer wall (created by the blown out
blanking plugs) of the bleed air supply
duct. This condition, if not corrected,
could result in heat damage to control
cables, electrical wiring, hydraulic
components, and fuel lines, and
consequent fire.
Relevant Service Information
Fokker Services B.V. has issued
Service Bulletin SBF50–36–006, dated
October 1, 2001. The service bulletin
describes the procedures for inspecting
zones 431 and 441 of the engine
controls area to determine if the
blanking plugs are installed in place on
the outer ducts of the bleed air supply
duct assemblies and doing corrective
actions if necessary. The corrective
actions include the following:
• If the blanking plugs are missing
and bleed air loss is evident (i.e., the
bleed air supply duct has burned spots,
discoloration, or deformation), visually
inspecting the components adjacent to
the bleed air supply duct assemblies for
heat damage (part C of the
accomplishment instructions) and
replacing the blanking plugs of the
bleed air supply duct with clamping
devices (part D of the accomplishment
instructions).
• If bleed air loss is not evident,
replacing the blanking plugs of the
bleed air supply duct with clamping
devices.
• If there is leakage from the bleed air
supply duct due to a ruptured inner
duct, replacing the bleed air supply duct
assembly with a serviceable bleed air
supply duct assembly (i.e, one that has
had the blanking plugs replaced with
clamping devices).
• If there is a loss of corrosionpreventing compound from the engine
control cables, cleaning the cables,
inspecting for discoloration, and
applying the corrosion-preventing
compound.
• If advice is needed for repairing
heat damage to a component, wiring, or
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
structures, contacting the manufacturer
for additional instructions.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition. The CAA–NL mandated the
service information and issued Dutch
airworthiness directive 2001–130, dated
October 31, 2001, to ensure the
continued airworthiness of these
airplanes in the Netherlands.
FAA’s Determination and Requirements
of This AD
This airplane models is manufactured
in the Netherlands and is type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. Pursuant to this bilateral
airworthiness agreement, the CAA–NL
has kept the FAA informed of the
situation described above. We have
examined the CAA–NL’s findings,
evaluated all pertinent information, and
determined that we need to issue an AD
for products of this type design that are
certificated for operation in the United
States.
Therefore, we are issuing this AD to
prevent rupture of the bleed air supply
duct, which could lead to hot bleed air
leaking into the engine controls area and
result in heat damage to control cables,
electrical wiring, hydraulic components,
and fuel lines, and consequent fire. This
AD requires accomplishing the actions
specified in the service information
described previously, except as
discussed under ‘‘Difference Between
the AD and Service Bulletin.’’
Difference Between the AD and Service
Bulletin
The service bulletin specifies to
contact the manufacturer for
instructions on how to repair certain
conditions, but this AD would require
repairing those conditions using a
method that we or the CAA–NL (or its
delegated agent) approve. In light of the
type of repair that would be required to
address the unsafe condition, and
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this AD, a repair we
or the CAA–NL approve would be
acceptable for compliance with this AD.
Clarification of Inspection Terminology
The inspection and ‘‘visual
inspection’’ specified in the Fokker
service bulletin is referred to as a
‘‘general visual inspection’’ in this AD.
We have included the definition for a
general visual inspection in a note in
this AD.
E:\FR\FM\16NOR1.SGM
16NOR1
Federal Register / Vol. 70, No. 220 / Wednesday, November 16, 2005 / Rules and Regulations
69429
Costs of Compliance
Examining the Docket
List of Subjects in 14 CFR Part 39
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
If an affected airplane is imported and
placed on the U.S. Register in the future,
the required actions would take about 3
work hours per airplane, at an average
labor rate of $65 per work hour. Based
on these figures, the estimated cost of
the AD would be $195 per airplane.
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2005–22972; Directorate Identifier
2003–NM–265–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that Web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
VerDate Aug<31>2005
11:21 Nov 15, 2005
Jkt 208001
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 have 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 that the 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 AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
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 Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2005–23–18 Fokker Services B.V.:
Amendment 39–14376. Docket No.
FAA–2005–22972; Directorate Identifier
2003–NM–265–AD.
Effective Date
(a) This AD becomes effective December 1,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Fokker Model
F27 Mark 050 airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from heat damage in
areas adjacent to the bleed air supply duct
assembly. We are issuing this AD to prevent
rupture of the bleed air supply duct, which
could lead to hot bleed air leaking into the
engine controls area and result in heat
damage to control cables, electrical wiring,
hydraulic components, and fuel lines, and
consequent fire.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
General Visual Inspection
(f) At the applicable compliance time
specified in paragraph (f)(1) or (f)(2) of this
AD, do a general visual inspection of the
bleed air supply to determine if blanking
plugs are present and a general visual
inspection of the entire area of the engine
nacelle for any heat damage, and do any
corrective actions as applicable, by
accomplishing all of the applicable actions
specified in parts B and C of the
Accomplishment Instructions of Fokker
Service Bulletin SBF50–36–006, dated
October 1, 2001; except as provided by
paragraph (g) of this AD. Any corrective
actions must be done before further flight.
E:\FR\FM\16NOR1.SGM
16NOR1
69430
Federal Register / Vol. 70, No. 220 / Wednesday, November 16, 2005 / Rules and Regulations
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
(1) For airplanes that have accumulated
20,000 total flight hours or more as of the
effective date of this AD: Within 6 months
after the effective date of this AD.
(2) For airplanes that have accumulated
less than 20,000 total flight hours as of the
effective date of this AD: Within 12 months
after the effective date of this AD.
(g) If, during accomplishment of the
corrective actions required by paragraph (f) of
this AD, the service bulletin requires
contacting the manufacturer for instructions
on repairing heat damage to a component,
wiring, or structure: Before further flight,
repair according to a method approved by
either the Manager, International Branch,
ANM–116, FAA, Transport Airplane
Directorate; or the Civil Aviation Authority—
The Netherlands (or its delegated agent).
Modification
(h) Before further flight after accomplishing
the inspection required by paragraph (f) of
this AD: Replace the blanking plugs of the
bleed air supply ducts with clamping
devices, in accordance with Part D of the
Accomplishment Instructions of Fokker
Service Bulletin SBF50–36–006, dated
October 1, 2001.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
Related Information
(j) Dutch airworthiness directive 2001–130,
dated October 31, 2001, also addresses the
subject of this AD.
Material Incorporated by Reference
(k) You must use Fokker Service Bulletin
SBF50–36–006, dated October 1, 2001, to
perform the actions that are required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference of this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact Fokker Services B.V., P.O.
Box 231, 2150 AE Nieuw-Vennep, the
Netherlands, for a copy of this service
VerDate Aug<31>2005
11:21 Nov 15, 2005
Jkt 208001
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 7, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–22589 Filed 11–15–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22427; Directorate
Identifier 2004–NM–263–AD; Amendment
39–14373; AD 2005–23–15]
RIN 2120–AA64
Airworthiness Directives; British
Aerospace Model BAC 1–11 200 and
400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
British Aerospace Model BAC 1–11 200
and 400 series airplanes. This AD
requires revising the airplane flight
manual (AFM) to contain applicable
AFM amendments, which advise the
flightcrew of information pertaining to
safely operating the fuel system. The AD
also requires revising the FAA-approved
maintenance program to include certain
repetitive maintenance tasks intended to
improve the safety of the fuel system.
This AD results from fuel system
reviews conducted by the manufacturer.
We are issuing this AD to prevent
potential ignition sources inside the fuel
system, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
DATES: This AD becomes effective
December 21, 2005.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of December 21, 2005.
ADDRESSES: You may examine the AD
docket on the Internet at https://
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, room PL–401,
Washington, DC.
Contact British Aerospace, Service
Support, Airbus Limited, P.O. Box 77,
Bristol BS99 7AR, England, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–1175; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to all British Aerospace Model
BAC 1–11 200 and 400 series airplanes.
That NPRM was published in the
Federal Register on September 16, 2005
(70 FR 54671). That NPRM proposed to
require revising the airplane flight
manual (AFM) to contain applicable
AFM amendments, which advise the
flightcrew of information pertaining to
safely operating the fuel system. The
NPRM also proposed to require revising
the FAA-approved maintenance
program to include certain repetitive
maintenance tasks intended to improve
the safety of the fuel system.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
E:\FR\FM\16NOR1.SGM
16NOR1
]]>Agencies
[Federal Register Volume 70, Number 220 (Wednesday, November 16, 2005)]
[Rules and Regulations]
[Pages 69427-69430]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-22589]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22972; Directorate Identifier 2003-NM-265-AD;
Amendment 39-14376; AD 2005-23-18]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
[[Page 69428]]
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Fokker Model F27 Mark 050 airplanes. This AD requires a one-time
inspection of the bleed air supply ducts to determine if blanking plugs
are present and a one-time inspection of the entire area of the engine
nacelle for heat damage; and corrective actions if necessary. This AD
also requires replacement of the blanking plugs with clamping devices.
This AD results from heat damage in areas adjacent to the bleed air
supply duct assembly. We are issuing this AD to prevent rupture of the
bleed air supply duct, which could lead to hot bleed air leaking into
the engine controls area and result in heat damage to control cables,
electrical wiring, hydraulic components, and fuel lines, and consequent
fire.
DATES: This AD becomes effective December 1, 2005.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 1,
2005.
We must receive comments on this AD by January 17, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep,
the Netherlands, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Authority--The Netherlands (CAA-NL), which is
the airworthiness authority for the Netherlands, notified us that an
unsafe condition may exist on all Fokker Model F27 Mark 050 airplanes.
The CAA-NL advises that an operator found heat damage in areas adjacent
to the bleed air supply duct assembly while inspecting for hydraulic
leakage in the engine controls area on a Model F27 Mark 050 airplane.
The same operator also found a second airplane with heat damage after
inspecting its remaining fleet. Further investigation revealed that the
inner wall of the bleed air supply duct was ruptured, which caused
bleed air to escape and blow out the three blanking plugs that are
fitted on the outer wall of the bleed air supply duct. As a result, hot
bleed air vented into the engine controls area through the holes in the
outer wall (created by the blown out blanking plugs) of the bleed air
supply duct. This condition, if not corrected, could result in heat
damage to control cables, electrical wiring, hydraulic components, and
fuel lines, and consequent fire.
Relevant Service Information
Fokker Services B.V. has issued Service Bulletin SBF50-36-006,
dated October 1, 2001. The service bulletin describes the procedures
for inspecting zones 431 and 441 of the engine controls area to
determine if the blanking plugs are installed in place on the outer
ducts of the bleed air supply duct assemblies and doing corrective
actions if necessary. The corrective actions include the following:
If the blanking plugs are missing and bleed air loss is
evident (i.e., the bleed air supply duct has burned spots,
discoloration, or deformation), visually inspecting the components
adjacent to the bleed air supply duct assemblies for heat damage (part
C of the accomplishment instructions) and replacing the blanking plugs
of the bleed air supply duct with clamping devices (part D of the
accomplishment instructions).
If bleed air loss is not evident, replacing the blanking
plugs of the bleed air supply duct with clamping devices.
If there is leakage from the bleed air supply duct due to
a ruptured inner duct, replacing the bleed air supply duct assembly
with a serviceable bleed air supply duct assembly (i.e, one that has
had the blanking plugs replaced with clamping devices).
If there is a loss of corrosion-preventing compound from
the engine control cables, cleaning the cables, inspecting for
discoloration, and applying the corrosion-preventing compound.
If advice is needed for repairing heat damage to a
component, wiring, or structures, contacting the manufacturer for
additional instructions.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The CAA-NL
mandated the service information and issued Dutch airworthiness
directive 2001-130, dated October 31, 2001, to ensure the continued
airworthiness of these airplanes in the Netherlands.
FAA's Determination and Requirements of This AD
This airplane models is manufactured in the Netherlands and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the CAA-NL has kept the FAA informed
of the situation described above. We have examined the CAA-NL's
findings, evaluated all pertinent information, and determined that we
need to issue an AD for products of this type design that are
certificated for operation in the United States.
Therefore, we are issuing this AD to prevent rupture of the bleed
air supply duct, which could lead to hot bleed air leaking into the
engine controls area and result in heat damage to control cables,
electrical wiring, hydraulic components, and fuel lines, and consequent
fire. This AD requires accomplishing the actions specified in the
service information described previously, except as discussed under
``Difference Between the AD and Service Bulletin.''
Difference Between the AD and Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this AD would
require repairing those conditions using a method that we or the CAA-NL
(or its delegated agent) approve. In light of the type of repair that
would be required to address the unsafe condition, and consistent with
existing bilateral airworthiness agreements, we have determined that,
for this AD, a repair we or the CAA-NL approve would be acceptable for
compliance with this AD.
Clarification of Inspection Terminology
The inspection and ``visual inspection'' specified in the Fokker
service bulletin is referred to as a ``general visual inspection'' in
this AD. We have included the definition for a general visual
inspection in a note in this AD.
[[Page 69429]]
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required actions would take about 3 work hours per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the estimated cost of the AD would be $195 per airplane.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2005-
22972; Directorate Identifier 2003-NM-265-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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 have 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 that the 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 AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-23-18 Fokker Services B.V.: Amendment 39-14376. Docket No. FAA-
2005-22972; Directorate Identifier 2003-NM-265-AD.
Effective Date
(a) This AD becomes effective December 1, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Fokker Model F27 Mark 050 airplanes,
certificated in any category.
Unsafe Condition
(d) This AD results from heat damage in areas adjacent to the
bleed air supply duct assembly. We are issuing this AD to prevent
rupture of the bleed air supply duct, which could lead to hot bleed
air leaking into the engine controls area and result in heat damage
to control cables, electrical wiring, hydraulic components, and fuel
lines, and consequent fire.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
General Visual Inspection
(f) At the applicable compliance time specified in paragraph
(f)(1) or (f)(2) of this AD, do a general visual inspection of the
bleed air supply to determine if blanking plugs are present and a
general visual inspection of the entire area of the engine nacelle
for any heat damage, and do any corrective actions as applicable, by
accomplishing all of the applicable actions specified in parts B and
C of the Accomplishment Instructions of Fokker Service Bulletin
SBF50-36-006, dated October 1, 2001; except as provided by paragraph
(g) of this AD. Any corrective actions must be done before further
flight.
[[Page 69430]]
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
(1) For airplanes that have accumulated 20,000 total flight
hours or more as of the effective date of this AD: Within 6 months
after the effective date of this AD.
(2) For airplanes that have accumulated less than 20,000 total
flight hours as of the effective date of this AD: Within 12 months
after the effective date of this AD.
(g) If, during accomplishment of the corrective actions required
by paragraph (f) of this AD, the service bulletin requires
contacting the manufacturer for instructions on repairing heat
damage to a component, wiring, or structure: Before further flight,
repair according to a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Civil Aviation Authority--The Netherlands (or its delegated
agent).
Modification
(h) Before further flight after accomplishing the inspection
required by paragraph (f) of this AD: Replace the blanking plugs of
the bleed air supply ducts with clamping devices, in accordance with
Part D of the Accomplishment Instructions of Fokker Service Bulletin
SBF50-36-006, dated October 1, 2001.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(j) Dutch airworthiness directive 2001-130, dated October 31,
2001, also addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use Fokker Service Bulletin SBF50-36-006, dated
October 1, 2001, to perform the actions that are required by this
AD, unless the AD specifies otherwise. The Director of the Federal
Register approved the incorporation by reference of this document in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Fokker
Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands,
for a copy of this service information. You may review copies at the
Docket Management Facility, U.S. Department of Transportation, 400
Seventh Street, SW., room PL-401, Nassif Building, Washington, DC;
on the Internet at https://dms.dot.gov; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at the NARA, call (202) 741-6030, or
go to https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on November 7, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-22589 Filed 11-15-05; 8:45 am]
BILLING CODE 4910-13-P
