[Federal Register Volume 75, Number 198 (Thursday, October 14, 2010)]
[Rules and Regulations]
[Pages 63042-63045]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-25449]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0479; Directorate Identifier 2009-NM-220-AD;
Amendment 39-16472; AD 2010-21-12]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Model F.28 Mark
0070 and 0100 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
* * * * *
Recently, a brake fire was reported which was caused by a
ruptured brake piston. The fire was quickly extinguished but caused
damage to the paint and hydraulic/electrical harness and its
components. Detailed investigation showed that a hydraulic lock must
have been present close to the affected brake creating enough
internal pressure to rupture the piston. The most probable scenario
for the hydraulic lock is a loosened (not necessarily disconnected)
brake QD [quick-disconnect] coupling. Further investigation of the
service experience files at Fokker Services showed that more brake
fires have occurred on aeroplanes in a pre-mod SBF100-32-127
configuration.
* * * * *
The unsafe condition is loss of braking capability and possible brake
fires, which could reduce the ability of the flightcrew to safely land
the airplane. We are issuing this AD to require actions to correct the
unsafe condition on these products.
DATES: This AD becomes effective November 18, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 18,
2010.
[[Page 63043]]
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on May 19, 2010 (75 FR
27961). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During 1995, several reports were received of brake QD [quick-
disconnect] couplings loosened and/or disconnected during operation.
In a few cases, residual brake pressure was trapped in the affected
brake, causing asymmetric braking and/or resulting in hot brakes.
Loosened couplings may cause a hydraulic leak with the risk of a
brake fire. Investigation revealed that the installation of the
brake QD couplings must be done with care and that the locking teeth
on the light alloy sleeve are prone to wear. The Fokker 70/100
Aircraft Maintenance Manual (AMM) has been revised to include
additional information to ensure correct removal and installation of
the couplings.
In 1997, Fokker Services issued SBF100-32-106, recommending the
introduction of QD couplings with corrosion resistant steel (CRES)
sleeves that would prevent excessive wear of the locking teeth on
the light alloy sleeve. In response to more reported cases of
loosened QD couplings resulting in brake problems, further improved
QD couplings were introduced in 2001 through SBF100-32-127. These
couplings increase the reliability of the brake system.
Recently, a brake fire was reported which was caused by a
ruptured brake piston. The fire was quickly extinguished but caused
damage to the paint and hydraulic/electrical harness and its
components. Detailed investigation showed that a hydraulic lock must
have been present close to the affected brake creating enough
internal pressure to rupture the piston. The most probable scenario
for the hydraulic lock is a loosened (not necessarily disconnected)
brake QD coupling. Further investigation of the service experience
files at Fokker Services showed that more brake fires have occurred
on aeroplanes in a pre-mod SBF100-32-127 configuration.
In order to reduce the probability of a fluid fire as described
in CS (certification specification) 25.863, additional action is
deemed necessary.
For the reasons described above, this [European Aviation Safety
Agency] AD requires repetitive [detailed] inspections [for wear] of
the affected brake QD couplings and replacement of the QD couplings
with improved units. Installation of the improved QD couplings
terminates the repetitive inspections requirements.
The unsafe condition is loss of braking capability and possible brake
fires, which could reduce the ability of the flightcrew to safely land
the airplane. You may obtain further information by examining the MCAI
in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 16 products of U.S. registry.
We also estimate that it will take about 4 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $4,814 per
product. Where the service information lists required parts costs that
are covered under warranty, we have assumed that there will be no
charge for these parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of this AD to the
U.S. operators to be $82,464, or $5,154 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
[[Page 63044]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2010-21-12 Fokker Services B.V.: Amendment 39-16472. Docket No. FAA-
2010-0479; Directorate Identifier 2009-NM-220-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
18, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Fokker Services B.V. Model F.28 Mark 0070
and 0100 airplanes, certificated in any category, all serial
numbers, with any brake quick-disconnect (QD) coupling having part
number (P/N) AE70690E, AE70691E, AE99111E, or AE99119E installed.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
Gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During 1995, several reports were received of brake QD couplings
loosened and/or disconnected during operation. In a few cases,
residual brake pressure was trapped in the affected brake, causing
asymmetric braking and/or resulting in hot brakes. Loosened
couplings may cause a hydraulic leak with the risk of a brake fire.
Investigation revealed that the installation of the brake QD
couplings must be done with care and that the locking teeth on the
light alloy sleeve are prone to wear. The Fokker 70/100 Aircraft
Maintenance Manual (AMM) has been revised to include additional
information to ensure correct removal and installation of the
couplings.
In 1997, Fokker Services issued SBF100-32-106, recommending the
introduction of QD couplings with corrosion resistant steel (CRES)
sleeves that would prevent excessive wear of the locking teeth on
the light alloy sleeve. In response to more reported cases of
loosened QD couplings resulting in brake problems, further improved
QD couplings were introduced in 2001 through SBF100-32-127. These
couplings increase the reliability of the brake system.
Recently, a brake fire was reported which was caused by a
ruptured brake piston. The fire was quickly extinguished but caused
damage to the paint and hydraulic/electrical harness and its
components. Detailed investigation showed that a hydraulic lock must
have been present close to the affected brake creating enough
internal pressure to rupture the piston. The most probable scenario
for the hydraulic lock is a loosened (not necessarily disconnected)
brake QD coupling. Further investigation of the service experience
files at Fokker Services showed that more brake fires have occurred
on aeroplanes in a pre-mod SBF100-32-127 configuration.
In order to reduce the probability of a fluid fire as described
in CS (certification specification) 25.863, additional action is
deemed necessary.
For the reasons described above, this [European Aviation Safety
Agency] AD requires repetitive [detailed] inspections [for wear] of
the affected brake QD couplings and replacement of the QD couplings
with improved units. Installation of the improved QD couplings
terminates the repetitive inspections requirements.
The unsafe condition is loss of braking capability and possible
brake fires, which could reduce the ability of the flightcrew to
safely land the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Actions
(g) Do the following actions.
(1) Within 6 months after the effective date of this AD, do a
detailed inspection for wear of the brake QD couplings by measuring
dimension ``A,'' in accordance with Part 1 of the Accomplishment
Instructions of Fokker Service Bulletin SBF100-32-156, Revision 1,
dated June 29, 2009. Repeat the inspection thereafter at the
applicable intervals specified in Table 1 of this AD, except as
required by paragraph (g)(2) of this AD.
Table 1--Repetitive Inspection Intervals
------------------------------------------------------------------------
Repeat the inspection at
If dimension ``A'' is-- intervals not to exceed--
------------------------------------------------------------------------
Greater than or equal to 0.76 mm............. 6 months.
Less than 0.76 mm but greater than or equal 3 months.
to 0.72 mm.
Less than 0.72 mm but greater than or equal 30 days.
to 0.68 mm.
Less than 0.68 mm but greater than or equal 7 days.
to 0.61 mm.
Less than 0.61 mm but greater than 0.53 mm... 24 hours.
------------------------------------------------------------------------
(2) If, during any inspection required by paragraph (g)(1) of
this AD, dimension ``A'' on any brake QD coupling is less than or
equal to 0.53 mm, before further flight, replace the affected brake
QD coupling with an improved unit having P/N AE73059E or P/N
AE73091E, as applicable, in accordance with Part 2 of the
Accomplishment Instructions of Fokker Service Bulletin SBF100-32-
156, Revision 1, dated June 29, 2009.
(3) Within 24 months after the effective date of this AD,
replace all remaining brake QD couplings having P/N AE70690E, P/N
AE70691E, P/N AE99111E, and P/N AE99119E with improved units, in
accordance with Part 2 of the Accomplishment Instructions of Fokker
Service Bulletin SBF100-32-156, Revision 1, dated June 29, 2009.
(4) Installation of brake QD couplings with an improved unit
having P/N AE73059E or P/N AE73091E at all locations terminates the
repetitive inspections required by paragraph (g)(1) of this AD.
(5) Replacing the brake QD couplings is also acceptable for
compliance with the corresponding requirements of paragraphs (g)(1),
(g)(2), and (g)(3) of this AD if done before the effective date of
this AD, in accordance with any of the service bulletins specified
in Table 2 of this AD:
[[Page 63045]]
Table 2--Fokker Credit Service Bulletins
------------------------------------------------------------------------
Fokker Service Bulletins Revision Date
------------------------------------------------------------------------
Fokker Performa Service Original........ July 20, 2001.
Bulletin SBF100-32-127,
including Appendix XIV, dated
February 1, 2006.
Fokker Performa Service 1............... March 6, 2009.
Bulletin SBF100-32-127,
including Appendix XIV, dated
February 1, 2006.
Fokker Service Bulletin SBF100- Original........ March 6, 2009.
32-156.
------------------------------------------------------------------------
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service
information as follows: No differences.
Other FAA AD Provisions
(h) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN: Tom
Rodriguez, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(i) Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2009-0176, dated August 6, 2009; and Fokker Service
Bulletin SBF100-32-156, Revision 1, dated June 29, 2009; for related
information.
Material Incorporated by Reference
(j) You must use Fokker Service Bulletin SBF100-32-156, Revision
1, dated June 29, 2009, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150
AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252-627-350; fax
+31 (0)252-627-211; e-mail
[email protected]; Internet http://www.myfokkerfleetcom.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on September 29, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-25449 Filed 10-13-10; 8:45 am]
BILLING CODE 4910-13-P