Airworthiness Directives; Fokker Model F27 Mark 500 Airplanes, 35572-35575 [E6-9714]
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35572
Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules
discharge automatically upon
occurrence of a fire in the receptacle.
16. Materials (including finishes or
decorative surfaces applied to the
materials) must comply with the
flammability requirements of § 25.853 at
Amendment 25–72. Mattresses must
comply with the flammability
requirements of § 25.853(b) and (c) at
Amendment 25–72.
17. All lavatories within the CRC are
required to meet the same requirements
as those for a lavatory installed on the
main deck except with regard to Special
Condition No.10 for smoke detection.
18. When a CRC is installed or
enclosed as a removable module in part
of a cargo compartment or is located
directly adjacent to a cargo
compartment without an intervening
cargo compartment wall, the following
apply:
(a) Any wall of the module (container)
forming part of the boundary of the
reduced cargo compartment, subject to
direct flame impingement from a fire in
the cargo compartment and including
any interface item between the module
(container) and the airplane structure or
systems, must meet the applicable
requirements of § 25.855 at Amendment
25–72.
(b) Means must be provided so that
the fire protection level of the cargo
compartment meets the applicable
requirements of § 25.855 at Amendment
25–72, § 25.857 at Amendment 25–60
and § 25.858 at Amendment 25–54
when the module (container) is not
installed.
(c) Use of each emergency evacuation
route must not require occupants of the
CRC compartment to enter the cargo
compartment in order to return to the
passenger compartment.
(d) The aural warning in Special
Condition No. 7 must sound in the CRC.
19. Means must be provided to
prevent access into the Class C cargo
compartment during all airplane flight
operations and to ensure that the
maintenance door is closed during all
airplane flight operations.
20. All enclosed stowage
compartments within the CRC that are
not limited to stowage of emergency
equipment or airplane-supplied
equipment (e.g., bedding) must meet the
design criteria given in the table below.
As indicated by the table below, this
special condition does not address
enclosed stowage compartments greater
than 200 ft 3 in interior volume. The inflight accessibility of very large enclosed
stowage compartments and the
subsequent impact on the crewmembers
ability to effectively reach any part of
the compartment with the contents of a
hand fire extinguisher will require
additional fire protection considerations
similar to those required for inaccessible
compartments such as Class C cargo
compartments.
STOWAGE COMPARTMENT INTERIOR VOLUMES
Fire protection features
Less than 25 ft 3
25 ft 3 to 57 ft 3
Materials of Construction 1 ....................................................................................
Detectors 2 .............................................................................................................
Liner 3 ....................................................................................................................
Locating Device 4 ...................................................................................................
Yes ........................
No .........................
No .........................
No .........................
Yes ........................
Yes ........................
No .........................
Yes ........................
57 ft 3 to 200 ft 3
Yes.
Yes
Yes.
Yes.
1 Material—The material used to construct each enclosed stowage compartment must at least be fire resistant and must meet the flammability
standards established for interior components per the requirements of § 25.853. For compartments less than 25 ft 3 in interior volume, the design
must ensure the ability to contain a fire likely to occur within the compartment under normal use.
2 Detectors—Enclosed stowage compartments equal to or exceeding 25 ft 3 in interior volume must be provided with a smoke or fire detection
system to ensure that a fire can be detected within a one-minute detection time. Flight tests must be conducted to show compliance with this requirement. Each system (or systems) must provide:
(a) A visual indication in the flightdeck within one minute after the start of a fire;
(b) An aural warning in the CRC; and
(c) A warning in the main passenger cabin. This warning must be readily detectable by a flight attendant, taking into consideration the positioning of flight attendants throughout the main passenger compartment during various phases of flight.
3 Liner—If it can be shown that the material used to construct the stowage compartment meets the flammability requirements of a liner for a
Class B cargo compartment, then no liner would be required for enclosed stowage compartments equal to or greater than 25 ft 3 in interior volume but less than 57 ft 3 in interior volume. For all enclosed stowage compartments equal to or greater than 57 ft 3 in interior volume but less
than or equal to 200 ft 3, a liner must be provided that meets the requirements of § 25.855 at Amendment 25–72 for a class B cargo compartment.
4 Location Detector—Crew rest areas which contain enclosed stowage compartments exceeding 25 ft 3 interior volume and which are located
away from one central location such as the entry to the crew rest area or a common area within the crew rest area would require additional fire
protection features and/or devices to assist the firefighter in determining the location of a fire.
Issued in Renton, Washington, on June 13,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–9819 Filed 6–20–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25086; Directorate
Identifier 2006–NM–019-AD]
RIN 2120–AA64
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Airworthiness Directives; Fokker
Model F27 Mark 500 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Fokker Model F27 Mark 500 airplanes.
This proposed AD would require an
inspection to determine whether certain
main landing gear (MLG) drag stay units
(DSUs) are installed. This proposed AD
would also require an ultrasonic
inspection to determine if certain tubes
are installed in the affected DSUs of the
MLG, and related investigative/
corrective actions if necessary. This
proposed AD results from a report that,
due to fatigue cracking from an
improperly machined radius of the
inner tube, a drag stay broke, and,
consequently, led to the collapse of the
MLG during landing. We are proposing
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Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules
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this AD to prevent such fatigue
cracking, which could result in reduced
structural integrity or collapse of the
MLG.
DATES: We must receive comments on
this proposed AD by July 21, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed 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 proposed 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:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–25086; Directorate
Identifier 2006–NM–019-AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
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 proposed 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
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16:40 Jun 20, 2006
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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.
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 certain Fokker
Model F27 Mark 500 airplanes. The
CAA–NL advises that it has received a
report that, due to a broken drag stay,
the main landing gear (MLG) on one
airplane collapsed during landing. The
broken drag stay is attributed to fatigue
cracking, which originated at the lower
side of a transition from a smaller
internal diameter on the upper piece to
a larger internal diameter on the lower
piece. The apparent cause of such
fatigue cracking has been attributed to
an improperly machined radius of the
inner tube of the drag stay. This
condition, if not corrected, could result
in reduced structural integrity or
collapse of the MLG.
The CAA–NL states that Dutch
airworthiness directive BLA 93–169/2
(A), dated April 29, 1994, was issued
following a similar incident to address
the identified unsafe condition on all
F27 airplanes. However, the related
Fokker Service Bulletin F27/32–167,
dated November 19, 1993, contained a
statement that may have led to
confusion whether Model F.27 Mark
500 airplanes were affected by the
actions specified in the service bulletin.
Thus, Model F27 Mark 500 airplanes
may be operating without fully
complying with actions necessary to
address the identified unsafe condition.
Other Relevant Rulemaking
On February 7, 1997, we issued AD
97–04–08, amendment 39–9932 (62 FR
7924, February 21, 1997), for certain
Fokker Model F27 Mark 050, 100, 200,
300, 400, 600, and 700 airplanes. That
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AD is parallel to Dutch airworthiness
directive BLA 93–169/2 (A), dated April
29, 1994, and does not include Model
F27 Mark 500 airplanes in its
applicability. AD 97–04–08 requires an
ultrasonic inspection to determine if
certain tubes are installed in the drag
stay units of the main landing gear
(MLG), and various follow-on actions.
That AD resulted from a report that, due
to fatigue cracking from an improperly
machined radius of the inner tube, a
drag stay broke, and, consequently, led
to the collapse of the MLG during
landing. We issued that AD to prevent
such fatigue cracking, which could
result in reduced structural integrity or
collapse of the MLG.
Relevant Service Information
Fokker Services B.V has issued
Fokker Service Bulletin F27/32–171,
dated December 16, 2004 (for Model F27
Mark 500 airplanes). The service
bulletin describes procedures for
performing an inspection of the MLG
drag stay units (DSUs) in accordance
with Dowty Aerospace Landing Gear
Service Bulletin 32–82W, Revision 2,
including Appendix A, dated July 29,
1994, and including Appendix B,
Revision 1, dated November 10, 1993; or
Dowty Aerospace Landing Gear Service
Bulletin 32–169B, Revision 2, including
Appendix A, dated July 29, 1994, and
including Appendix B, Revision 1,
dated November 10, 1993.
Dowty Aerospace Landing Gear
Service Bulletins 32–82W and 32–169B
describe procedures for performing an
ultrasonic inspection to determine if a
tube having part number (P/N)
200485300 with a straight bore, or a
tube having P/N 200259300 with a
change in section (stepped bore), is
installed in the DSUs of the MLG. The
service bulletins also describe
procedures for related investigative
actions and corrective actions, including
ultrasonic inspection for cracking of the
DSUs, rework and re-identification of
certain tubes, replacement of certain
DSUs with new/re-identified DSUs, and
repetitive ultrasonic inspections of
certain DSUs. Both service bulletins
include the ultrasonic inspection to
determine P/Ns for DSUs having P/N
200485001. Service bulletin 32–82W
also addresses the ultrasonic inspection
for DSUs having P/N 200684001.
Service Bulletin 32–169B also addresses
the ultrasonic inspection for DSUs
having P/N 200261001.
CAA–NL mandated the service
information and issued airworthiness
directive NL–2005–003, dated April 29,
2005, to ensure the continued
airworthiness of these airplanes in the
Netherlands.
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Federal Register / Vol. 71, No. 119 / Wednesday, June 21, 2006 / Proposed Rules
FAA’s Determination and Requirements
of the Proposed AD
This airplane model 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, 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
airplanes this type design that are
certificated for operation in the United
States.
Therefore, we are proposing this AD,
which would require accomplishing the
actions specified in the service
information described previously.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Action
Work hours
Average labor
rate per hour
Cost per airplane
Number of
U.S.-registered
airplanes
Fleet cost
Inspection .............................................................................
2
$80
$160
7
$1,120
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.
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Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Fokker Services B.V.: Docket No. FAA–
2006–25086; Directorate Identifier 2006–
NM–019–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by July 21, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Fokker Model
F27 Mark 500 airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from a report that, due
to fatigue cracking from an improperly
machined radius of the inner tube, a drag
stay broke, and, consequently, led to the
collapse of the MLG during landing. We are
issuing this AD to prevent such fatigue
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cracking, which could result in reduced
structural integrity or collapse of the MLG.
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.
Inspections of the DSUs
(f) Within 60 days after the effective date
of this AD: Inspect main landing gear (MLG)
drag stay units (DSU) to determine whether
Dowty Aerospace is the manufacturer and
before further flight inspect Dowty Aerospace
MLG DSUs to determine whether part
number (P/N) 200261001, 200261002,
200485001, 200485002, 200684001, or
200684002 is installed. A review of airplane
maintenance records is acceptable in lieu of
these inspections if the manufacturer and
P/N of the MLG DSU can be conclusively
determined from that review. For airplanes
equipped with MLG DSUs other than Dowty
Aerospace MLG DSUs, and for airplanes
equipped with Dowty Aerospace MLG DSUs
having P/Ns other than P/N 200261001,
200261002, 200485001, 200485002,
200684001, and 200684002, no further action
is required by this AD, except as specified in
paragraph (k) of this AD.
(g) For airplanes equipped with DSUs
having P/N 200261001, 200485001, or
200684001: Within 60 days after the effective
date of this AD, perform an ultrasonic
inspection to determine if a tube having
P/N 200485300 with a straight bore, or a tube
having P/N 200259300 with a change in
section (stepped bore), is installed on the
DSUs of the MLG, in accordance with the
Accomplishment Instructions of Fokker
Service Bulletin F27/32–171, dated
December 16, 2004.
Note 1: Fokker Service Bulletin F27/32–
171, dated December 16, 2004, references
Dowty Aerospace Landing Gear Service
Bulletin 32–82W, Revision 2, including
Appendix A, dated July 29, 1994, and
including Appendix B, Revision 1, dated
November 10, 1993; and Dowty Aerospace
Landing Gear Service Bulletin 32–169B,
Revision 2, including Appendix A, dated July
29, 1994, and including Appendix B,
Revision 1, dated November 10, 1993; as
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applicable, as appropriates sources of service
information for inspecting MLG DSUs.
(h) If any tube having P/N 200485300 with
a straight bore is found installed during the
inspections required by paragraph (g) of this
AD: Before further flight, re-identify the DSU
with P/N 200261004, 200485004, or
200684004, in accordance with the
Accomplishment Instructions of Dowty
Aerospace Landing Gear Service Bulletin 32–
82W, Revision 2, including Appendix A,
dated July 29, 1994, and including Appendix
B, Revision 1, dated November 10, 1993; or
Dowty Aerospace Landing Gear Service
Bulletin 32–169B, Revision 2, including
Appendix A, dated July 29, 1994, and
including Appendix B, Revision 1, dated
November 10, 1993; as applicable. After reidentifying the DSU, no further action is
required by this AD for that DSU; however
airplanes are still subject to the requirements
specified in paragraph (k) of this AD.
(i) If any tube having P/N 200259300 with
a change in section (stepped bore) is found
installed during the inspection required by
paragraph (g) of this AD: Before further flight,
re-identify the DSU in accordance with
paragraphs 2.A.(4)(a) and 2.A.(4)(b) of the
Accomplishment Instructions Dowty
Aerospace Landing Gear Service Bulletin 32–
82W, Revision 2, including Appendix A,
dated July 29, 1994, and including Appendix
B, Revision 1, dated November 10, 1993; or
Dowty Aerospace Landing Gear Service
Bulletin 32–169B, Revision 2, including
Appendix A, dated July 29, 1994, and
including Appendix B, Revision 1, dated
November 10, 1993; as applicable. Following
accomplishment of the re-identification,
before further flight, do the inspection
specified in paragraph (j) of this AD.
Ultrasonic Inspection for Cracking
(j) For airplanes equipped with reidentified DSUs having 200261002,
200485002, 200684002, 200261003,
200485003, or 200684003: Within 60 days
after the effective date of this AD, perform an
ultrasonic inspection to detect cracking in
the re-identified DSUs, in accordance with
the Accomplishment Instructions of Dowty
Aerospace Landing Gear Service Bulletin 32–
82W, Revision 2, including Appendix A,
dated July 29, 1994, and including Appendix
B, Revision 1, dated November 10, 1993; or
Dowty Aerospace Landing Gear Service
Bulletin 32–169B, Revision 2, including
Appendix A, dated July 29, 1994, and
including Appendix B, Revision 1, dated
November 10, 1993; as applicable.
(1) For airplanes equipped with any DSU
re-identified as P/N 200684003, 200261003,
or 200485003: If no crack is detected, no
further action is required by this AD for that
DSU; however airplanes are still subject to
the requirements specified in paragraph (k) of
this AD.
(2) For airplanes equipped with any DSU
re-identified as P/N 200684002, 200261002,
or 200485002: If no crack is detected, do the
actions specified in paragraphs (j)(2)(i) and
(j)(2)(ii) of this AD.
(i) Repeat the ultrasonic inspection
required by paragraph (j) of this AD thereafter
at intervals not to exceed 1,500 flight cycles
until the actions specified in paragraph
(j)(2)(ii) of this AD are done.
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(ii) At the next MLG overhaul but no later
than 12,000 flight cycles after the effective
date of this AD, rework and re-identify the
DSU as P/N 200261003, 200485003, or
200684003, as applicable, in accordance with
the applicable service bulletin.
(3) If any crack is detected and the crack
signal indication of any DSU tube is greater
than or equal to 80 percent, before further
flight, replace the DSU with a re-identified
DSU having P/N 200261004, 200485004,
200684004, 200261003, 200485003, or
200684003, in accordance with the
applicable service bulletin.
(4) If any crack is detected and the crack
signal indication of any DSU tube is greater
than zero percent but less than 80 percent,
do the actions specified in paragraphs (j)(4)(i)
and (j)(4)(ii) of this AD.
(i) Repeat the ultrasonic inspection
required by paragraph (j) of this AD thereafter
at intervals not to exceed 1,500 flight cycles
until the actions specified in paragraph
(j)(4)(ii) of this AD are done.
(ii) At the next MLG overhaul but no later
than 12,000 flight cycles after the effective
date of this AD, replace the DSU with a DSU
having P/N 200261004, 200485004,
200684004, 200261003, 200485003, or
200684003, in accordance with the
applicable service bulletin.
35575
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25088; Directorate
Identifier 2006 NM–085–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–600, B4–600R, and F4–600R
Series Airplanes, and Model A300 C4–
605R Variant F Airplanes (Collectively
Called A300–600 Series Airplanes)
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Airbus Model A300–600 series
airplanes. The existing AD currently
requires an inspection for evidence of
chafing between the hydraulic flexible
hose and the ram air turbine (RAT) hub,
and related investigative and corrective
actions if necessary. This proposed AD
would extend the applicability to
Parts Installation
include all A300–600 series airplanes
(k) As of the effective date of this AD, no
that are equipped with a certain RAT.
person may install a MLG DSU, P/N
This proposed AD results from reports
200261001, 200261002, 200485001,
of holes in the RAT hub cover. We are
200485002, 200684001, or 200684002, on any
proposing this AD to prevent a hole in
airplane, except as specified in paragraph (i)
the RAT hub cover. A hole in the RAT
of this AD.
hub cover could allow water to enter the
RAT governing mechanism, freeze
Alternative Methods of Compliance
(AMOCs)
during flight, and jam the governing
mechanism. In addition, the metal
(l)(1) The Manager, International Branch,
particles that result from chafing
ANM–116, Transport Airplane Directorate,
between the hydraulic flexible hose and
FAA, has the authority to approve AMOCs
the RAT could mix with the lubricant
for this AD, if requested in accordance with
grease and degrade the governing
the procedures found in 14 CFR 39.19.
mechanism. In an emergency, a jammed
(2) Before using any AMOC approved in
or degraded RAT could result in its
accordance with § 39.19 on any airplane to
failure to deploy, loss of hydraulic
which the AMOC applies, notify the
pressure or electrical power to the
appropriate principal inspector in the FAA
airplane, and consequent reduced
Flight Standards Certificate Holding District
controllability of the airplane.
Office.
DATES: We must receive comments on
Related Information
this proposed AD by July 21, 2006.
(m) Dutch airworthiness directive NL–
ADDRESSES: Use one of the following
2005–003, dated April 29, 2005, also
addresses to submit comments on this
addresses the subject of this AD.
proposed AD.
• DOT Docket Web site: Go to
Issued in Renton, Washington, on June 14,
https://dms.dot.gov and follow the
2006.
instructions for sending your comments
Kalene C. Yanamura,
electronically.
Acting Manager, Transport Airplane
• Government-wide rulemaking Web
Directorate, Aircraft Certification Service.
site: Go to https://www.regulations.gov
[FR Doc. E6–9714 Filed 6–20–06; 8:45 am]
and follow the instructions for sending
BILLING CODE 4910–13–P
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
PO 00000
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Agencies
[Federal Register Volume 71, Number 119 (Wednesday, June 21, 2006)]
[Proposed Rules]
[Pages 35572-35575]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-9714]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25086; Directorate Identifier 2006-NM-019-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F27 Mark 500 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Fokker Model F27 Mark 500 airplanes. This proposed AD would
require an inspection to determine whether certain main landing gear
(MLG) drag stay units (DSUs) are installed. This proposed AD would also
require an ultrasonic inspection to determine if certain tubes are
installed in the affected DSUs of the MLG, and related investigative/
corrective actions if necessary. This proposed AD results from a report
that, due to fatigue cracking from an improperly machined radius of the
inner tube, a drag stay broke, and, consequently, led to the collapse
of the MLG during landing. We are proposing
[[Page 35573]]
this AD to prevent such fatigue cracking, which could result in reduced
structural integrity or collapse of the MLG.
DATES: We must receive comments on this proposed AD by July 21, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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 proposed
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:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
25086; Directorate Identifier 2006-NM-019-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
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 proposed 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.
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 certain Fokker Model F27 Mark 500
airplanes. The CAA-NL advises that it has received a report that, due
to a broken drag stay, the main landing gear (MLG) on one airplane
collapsed during landing. The broken drag stay is attributed to fatigue
cracking, which originated at the lower side of a transition from a
smaller internal diameter on the upper piece to a larger internal
diameter on the lower piece. The apparent cause of such fatigue
cracking has been attributed to an improperly machined radius of the
inner tube of the drag stay. This condition, if not corrected, could
result in reduced structural integrity or collapse of the MLG.
The CAA-NL states that Dutch airworthiness directive BLA 93-169/2
(A), dated April 29, 1994, was issued following a similar incident to
address the identified unsafe condition on all F27 airplanes. However,
the related Fokker Service Bulletin F27/32-167, dated November 19,
1993, contained a statement that may have led to confusion whether
Model F.27 Mark 500 airplanes were affected by the actions specified in
the service bulletin. Thus, Model F27 Mark 500 airplanes may be
operating without fully complying with actions necessary to address the
identified unsafe condition.
Other Relevant Rulemaking
On February 7, 1997, we issued AD 97-04-08, amendment 39-9932 (62
FR 7924, February 21, 1997), for certain Fokker Model F27 Mark 050,
100, 200, 300, 400, 600, and 700 airplanes. That AD is parallel to
Dutch airworthiness directive BLA 93-169/2 (A), dated April 29, 1994,
and does not include Model F27 Mark 500 airplanes in its applicability.
AD 97-04-08 requires an ultrasonic inspection to determine if certain
tubes are installed in the drag stay units of the main landing gear
(MLG), and various follow-on actions. That AD resulted from a report
that, due to fatigue cracking from an improperly machined radius of the
inner tube, a drag stay broke, and, consequently, led to the collapse
of the MLG during landing. We issued that AD to prevent such fatigue
cracking, which could result in reduced structural integrity or
collapse of the MLG.
Relevant Service Information
Fokker Services B.V has issued Fokker Service Bulletin F27/32-171,
dated December 16, 2004 (for Model F27 Mark 500 airplanes). The service
bulletin describes procedures for performing an inspection of the MLG
drag stay units (DSUs) in accordance with Dowty Aerospace Landing Gear
Service Bulletin 32-82W, Revision 2, including Appendix A, dated July
29, 1994, and including Appendix B, Revision 1, dated November 10,
1993; or Dowty Aerospace Landing Gear Service Bulletin 32-169B,
Revision 2, including Appendix A, dated July 29, 1994, and including
Appendix B, Revision 1, dated November 10, 1993.
Dowty Aerospace Landing Gear Service Bulletins 32-82W and 32-169B
describe procedures for performing an ultrasonic inspection to
determine if a tube having part number (P/N) 200485300 with a straight
bore, or a tube having P/N 200259300 with a change in section (stepped
bore), is installed in the DSUs of the MLG. The service bulletins also
describe procedures for related investigative actions and corrective
actions, including ultrasonic inspection for cracking of the DSUs,
rework and re-identification of certain tubes, replacement of certain
DSUs with new/re-identified DSUs, and repetitive ultrasonic inspections
of certain DSUs. Both service bulletins include the ultrasonic
inspection to determine P/Ns for DSUs having P/N 200485001. Service
bulletin 32-82W also addresses the ultrasonic inspection for DSUs
having P/N 200684001. Service Bulletin 32-169B also addresses the
ultrasonic inspection for DSUs having P/N 200261001.
CAA-NL mandated the service information and issued airworthiness
directive NL-2005-003, dated April 29, 2005, to ensure the continued
airworthiness of these airplanes in the Netherlands.
[[Page 35574]]
FAA's Determination and Requirements of the Proposed AD
This airplane model 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, 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 airplanes this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Cost per registered Fleet cost
rate per hour airplane airplanes
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Inspection......................................................... 2 $80 $160 7 $1,120
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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 have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Fokker Services B.V.: Docket No. FAA-2006-25086; Directorate
Identifier 2006-NM-019-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 21,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Fokker Model F27 Mark 500 airplanes,
certificated in any category.
Unsafe Condition
(d) This AD results from a report that, due to fatigue cracking
from an improperly machined radius of the inner tube, a drag stay
broke, and, consequently, led to the collapse of the MLG during
landing. We are issuing this AD to prevent such fatigue cracking,
which could result in reduced structural integrity or collapse of
the MLG.
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.
Inspections of the DSUs
(f) Within 60 days after the effective date of this AD: Inspect
main landing gear (MLG) drag stay units (DSU) to determine whether
Dowty Aerospace is the manufacturer and before further flight
inspect Dowty Aerospace MLG DSUs to determine whether part number
(P/N) 200261001, 200261002, 200485001, 200485002, 200684001, or
200684002 is installed. A review of airplane maintenance records is
acceptable in lieu of these inspections if the manufacturer and P/N
of the MLG DSU can be conclusively determined from that review. For
airplanes equipped with MLG DSUs other than Dowty Aerospace MLG
DSUs, and for airplanes equipped with Dowty Aerospace MLG DSUs
having P/Ns other than P/N 200261001, 200261002, 200485001,
200485002, 200684001, and 200684002, no further action is required
by this AD, except as specified in paragraph (k) of this AD.
(g) For airplanes equipped with DSUs having P/N 200261001,
200485001, or 200684001: Within 60 days after the effective date of
this AD, perform an ultrasonic inspection to determine if a tube
having P/N 200485300 with a straight bore, or a tube having P/N
200259300 with a change in section (stepped bore), is installed on
the DSUs of the MLG, in accordance with the Accomplishment
Instructions of Fokker Service Bulletin F27/32-171, dated December
16, 2004.
Note 1: Fokker Service Bulletin F27/32-171, dated December 16,
2004, references Dowty Aerospace Landing Gear Service Bulletin 32-
82W, Revision 2, including Appendix A, dated July 29, 1994, and
including Appendix B, Revision 1, dated November 10, 1993; and Dowty
Aerospace Landing Gear Service Bulletin 32-169B, Revision 2,
including Appendix A, dated July 29, 1994, and including Appendix B,
Revision 1, dated November 10, 1993; as
[[Page 35575]]
applicable, as appropriates sources of service information for
inspecting MLG DSUs.
(h) If any tube having P/N 200485300 with a straight bore is
found installed during the inspections required by paragraph (g) of
this AD: Before further flight, re-identify the DSU with P/N
200261004, 200485004, or 200684004, in accordance with the
Accomplishment Instructions of Dowty Aerospace Landing Gear Service
Bulletin 32-82W, Revision 2, including Appendix A, dated July 29,
1994, and including Appendix B, Revision 1, dated November 10, 1993;
or Dowty Aerospace Landing Gear Service Bulletin 32-169B, Revision
2, including Appendix A, dated July 29, 1994, and including Appendix
B, Revision 1, dated November 10, 1993; as applicable. After re-
identifying the DSU, no further action is required by this AD for
that DSU; however airplanes are still subject to the requirements
specified in paragraph (k) of this AD.
(i) If any tube having P/N 200259300 with a change in section
(stepped bore) is found installed during the inspection required by
paragraph (g) of this AD: Before further flight, re-identify the DSU
in accordance with paragraphs 2.A.(4)(a) and 2.A.(4)(b) of the
Accomplishment Instructions Dowty Aerospace Landing Gear Service
Bulletin 32-82W, Revision 2, including Appendix A, dated July 29,
1994, and including Appendix B, Revision 1, dated November 10, 1993;
or Dowty Aerospace Landing Gear Service Bulletin 32-169B, Revision
2, including Appendix A, dated July 29, 1994, and including Appendix
B, Revision 1, dated November 10, 1993; as applicable. Following
accomplishment of the re-identification, before further flight, do
the inspection specified in paragraph (j) of this AD.
Ultrasonic Inspection for Cracking
(j) For airplanes equipped with re-identified DSUs having
200261002, 200485002, 200684002, 200261003, 200485003, or 200684003:
Within 60 days after the effective date of this AD, perform an
ultrasonic inspection to detect cracking in the re-identified DSUs,
in accordance with the Accomplishment Instructions of Dowty
Aerospace Landing Gear Service Bulletin 32-82W, Revision 2,
including Appendix A, dated July 29, 1994, and including Appendix B,
Revision 1, dated November 10, 1993; or Dowty Aerospace Landing Gear
Service Bulletin 32-169B, Revision 2, including Appendix A, dated
July 29, 1994, and including Appendix B, Revision 1, dated November
10, 1993; as applicable.
(1) For airplanes equipped with any DSU re-identified as P/N
200684003, 200261003, or 200485003: If no crack is detected, no
further action is required by this AD for that DSU; however
airplanes are still subject to the requirements specified in
paragraph (k) of this AD.
(2) For airplanes equipped with any DSU re-identified as P/N
200684002, 200261002, or 200485002: If no crack is detected, do the
actions specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) Repeat the ultrasonic inspection required by paragraph (j)
of this AD thereafter at intervals not to exceed 1,500 flight cycles
until the actions specified in paragraph (j)(2)(ii) of this AD are
done.
(ii) At the next MLG overhaul but no later than 12,000 flight
cycles after the effective date of this AD, rework and re-identify
the DSU as P/N 200261003, 200485003, or 200684003, as applicable, in
accordance with the applicable service bulletin.
(3) If any crack is detected and the crack signal indication of
any DSU tube is greater than or equal to 80 percent, before further
flight, replace the DSU with a re-identified DSU having P/N
200261004, 200485004, 200684004, 200261003, 200485003, or 200684003,
in accordance with the applicable service bulletin.
(4) If any crack is detected and the crack signal indication of
any DSU tube is greater than zero percent but less than 80 percent,
do the actions specified in paragraphs (j)(4)(i) and (j)(4)(ii) of
this AD.
(i) Repeat the ultrasonic inspection required by paragraph (j)
of this AD thereafter at intervals not to exceed 1,500 flight cycles
until the actions specified in paragraph (j)(4)(ii) of this AD are
done.
(ii) At the next MLG overhaul but no later than 12,000 flight
cycles after the effective date of this AD, replace the DSU with a
DSU having P/N 200261004, 200485004, 200684004, 200261003,
200485003, or 200684003, in accordance with the applicable service
bulletin.
Parts Installation
(k) As of the effective date of this AD, no person may install a
MLG DSU, P/N 200261001, 200261002, 200485001, 200485002, 200684001,
or 200684002, on any airplane, except as specified in paragraph (i)
of this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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 Sec.
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
(m) Dutch airworthiness directive NL-2005-003, dated April 29,
2005, also addresses the subject of this AD.
Issued in Renton, Washington, on June 14, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-9714 Filed 6-20-06; 8:45 am]
BILLING CODE 4910-13-P