Airworthiness Directives; Fokker Services B.V. Airplanes, 68052-68055 [2012-26781]
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Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations
been repaired as specified in an Airbus
structural repair manual or repair approval
sheet as of the effective date of this AD:
Before the accumulation of 10,000 total flight
cycles since first flight of the airplane, or
within 600 flight cycles after the effective
date of this AD, whichever occurs later,
perform a high frequency eddy current
(HFEC) inspection for cracking of the
crossbeam fuselage frame stations FR 22/23
and FR 61/62, in accordance with the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of
this AD. Repeat the inspection thereafter at
intervals not to exceed 600 flight cycles until
the modification specified in paragraph (i) of
this AD has been done.
(i) Airbus Mandatory Service Bulletin
A300–53–0390, dated January 15, 2010 (for
Model A300 series airplanes).
(ii) Airbus Mandatory Service Bulletin
A310–53–2134, dated January 15, 2010 (for
Model A310 series airplanes).
(iii) Airbus Mandatory Service Bulletin
A300–53–6168, dated January 15, 2010 (for
Model A300–600 series airplanes).
(2) For airplanes on which the crossbeams
at FR 22/23 and FR 61/62 have been repaired
as specified in an Airbus structural repair
manual or repair approval sheet as of the
effective date of this AD: Before the
accumulation of 10,000 total flight cycles
since first flight of the airplane, or within 600
flight cycles after the effective date of this
AD, whichever occurs later, repair in
accordance with a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA) (or
its delegated agent).
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(h) Corrective Action
If any crack is found during any inspection
required by paragraph (g) of this AD: Before
further flight, repair any crack using a
method approved by the Manager,
International Branch, ANM–116; or EASA (or
its delegated agent).
(i) Optional Terminating Action
Modifying the crossbeam fuselage frame
stations FR 22/23 and FR 61/62, including
doing rotating probe inspections for cracks of
fastener holes, in accordance with the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (i)(1), (i)(2), or (i)(3) of this AD,
and repairing any crack using a method
approved by the Manager, International
Branch, ANM–116; or EASA (or its delegated
agent); terminates the repetitive inspections
required by paragraph (g)(1) of this AD.
(1) Airbus Service Bulletin A300–53–0389,
Revision 02, dated April 27, 2011 (for Model
A300 series airplanes).
(2) Airbus Service Bulletin A310–53–2133,
Revision 02, dated April 27, 2011 (for Model
A310 series airplanes).
(3) Airbus Service Bulletin A300–53–6166,
Revision 01, dated May 21, 2010 (for Model
A300–600 series airplanes).
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
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13:24 Nov 14, 2012
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(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.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–2125; fax (425)
227–1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding 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.
(k) Related Information
Refer to EASA Airworthiness Directive
2011–0086, dated May 12, 2011; and the
service information identified in paragraphs
(k)(1), (k)(2), (k)(3), (k)(4), (k)(5), and (k)(6) of
this AD, for related information.
(1) Airbus Mandatory Service Bulletin
A300–53–0390, dated January 15, 2010.
(2) Airbus Mandatory Service Bulletin
A300–53–6168, dated January 15, 2010.
(3) Airbus Mandatory Service Bulletin
A310–53–2134, dated January 15, 2010.
(4) Airbus Service Bulletin A300–53–0389,
Revision 02, dated April 27, 2011.
(5) Airbus Service Bulletin A300–53–6166,
Revision 01, dated May 21, 2010.
(6) Airbus Service Bulletin A310–53–2133,
Revision 02, dated April 27, 2011.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Mandatory Service Bulletin
A300–53–0390, dated January 15, 2010.
(ii) Airbus Mandatory Service Bulletin
A300–53–6168, dated January 15, 2010.
(iii) Airbus Mandatory Service Bulletin
A310–53–2134, dated January 15, 2010.
(iv) Airbus Service Bulletin A300–53–
0389, Revision 02, dated April 27, 2011.
(v) Airbus Service Bulletin A300–53–6166,
Revision 01, dated May 21, 2010.
(vi) Airbus Service Bulletin A310–53–
2133, Revision 02, dated April 27, 2011.
(3) For service information identified in
this AD, contact Airbus SAS—EAW
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(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com.
(4) You may review copies of the
referenced 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.
(5) You may view this 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on October
24, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–27055 Filed 11–14–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0643; Directorate
Identifier 2011–NM–190–AD; Amendment
39–17241; AD 2012–22–05]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain Fokker Services B.V. Model F.28
Mark 0070 and 0100 airplanes. That AD
currently requires performing a detailed
visual inspection for cracks of the
pistons on the main landing gear (MLG),
and replacing the affected pistons if
necessary. This new AD also requires
modifying the MLG by installing a
piston containing a certain part number,
and revising the airplane maintenance
program. This AD was prompted by a
new modification developed to
safeguard the integrity of the MLG
assembly and improve surface
protection of the affected area of the
MLG piston. We are issuing this AD to
prevent MLG failure, possibly resulting
in loss of control of the airplane during
the landing roll-out.
DATES: This AD becomes effective
December 20, 2012.
SUMMARY:
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Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 20, 2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of March 22, 2011 (76 FR
8618, February 15, 2011).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: 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
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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 June 21, 2012 (77 FR 37337),
and proposed to supersede AD 2011–
04–01, Amendment 39–16601 (76 FR
8618, February 15, 2011). That NPRM
proposed to correct an unsafe condition
for the specified products. The
Mandatory Continuing Airworthiness
Information (MCAI) states:
During a normal walk around check on a
F28 Mark 0100 aeroplane, a large crack was
discovered in the lower portion of the right
(RH) MLG piston. The affected MLG unit had
accumulated 7,909 flight cycles (FC) at the
time of detection. The piston was sent to
Goodrich, the landing gear manufacturer, for
detailed investigation, which revealed that
the crack had been initiated by corrosion
pits. The extent of the corrosion indicates
that the initial crack existed for a substantial
period before a high loading event caused the
crack to grow further by ductile overload.
This condition, if not detected and
corrected, could lead to MLG failure during
the landing roll-out, possibly resulting in
damage to the aeroplane and injury to
occupants.
To address this potential unsafe condition,
EASA [European Aviation Safety Agency]
issued AD 2009–0221 [which corresponds
with FAA AD 2011–04–01, Amendment 39–
16601 (76 FR 8618, February 15, 2011)] to
require a one-time detailed visual inspection
of the MLG pistons, the replacement of any
MLG pistons on which cracks are detected,
and the reporting of all findings to the
aeroplane TC [type certificate] holder. No
cracks were reported as a result of this
inspection.
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Subsequently, a repetitive inspection was
introduced in the Airworthiness Limitations
Section (Fokker Services report SE–623 Issue
8) in Appendix 1 of the Maintenance Review
Board (MRB) document to safeguard the
integrity of the MLG assembly, pending the
accomplishment of a terminating action.
Goodrich issued Service Bulletin (SB)
41000–32–29 to introduce an improved
surface protection (nickel plate) of the
affected area of the MLG piston P/N [part
number] 41141–3 and re-identification as P/
N 41141–5, which is considered as a
terminating action for the repetitive
inspections.
For the reasons described above, this
[EASA] AD requires repetitive visual
inspections of the P/N 41141–3 MLG piston
for cracks and, depending on findings,
replacement or modification of the MLG
piston. This [EASA] AD also requires
modification of the affected MLG by
installing a piston P/N 41141–5.
You may obtain further information by
examining the MCAI in the AD docket.
Change Made to This AD
We have revised paragraphs (k), (l),
and (n), of this final rule to clarify the
document citation of Fokker Report SE–
623 to meet the Office of Federal
Register’s guidelines for materials
incorporated by reference. There is no
change to the requirements specified in
those paragraphs.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (77
FR 37337, June 21, 2012) 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—except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (77 FR
37337, June 21, 2012) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (77 FR 37337,
June 21, 2012).
Costs of Compliance
We estimate that this AD will affect
about 2 products of U.S. registry.
The actions that are required by AD
2011–04–01, Amendment 39–16601 (76
FR 8618, February 15, 2011), and
retained in this AD take about 3 workhours per product, at an average labor
rate of $85 per work-hour. Based on
these figures, the estimated cost of the
currently required actions is $255 per
product.
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68053
We estimate that it will take about 24
work-hours per product to comply with
the new basic requirements of this AD.
The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of this AD to the U.S.
operators to be $4,080, or $2,040 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 that 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);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
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Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations
contains the NPRM (77 FR 37337, June
21, 2012), the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2011–04–01, Amendment 39–16601 (76
FR 8618, February 15, 2011), and adding
the following new AD:
■
2012–22–05 Fokker Services B.V.:
Amendment 39–17241. Docket No.
FAA–2012–0643; Directorate Identifier
2011–NM–190–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective December 20, 2012.
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(b) Affected ADs
This AD supersedes AD 2011–04–01,
Amendment 39–16601 (76 FR 8618, February
15, 2011).
(c) Applicability
(1) This AD applies to Fokker Services B.V.
Model F.28 Mark 0070 and 0100 airplanes,
certificated in any category, all serial
numbers, equipped with Goodrich (formerly
Menasco, Colt Industries) main landing gear
(MLG) units, part numbers (P/N) 41050–7,
41050–8, 41050–9, 41050–10, 41050–11,
41050–12, 41050–13, 41050–14, 41050–15,
41050–16, 41060–1, 41060–2, 41060–3,
41060–4, 41060–5, or 41060–6.
(2) This AD requires revisions to certain
operator maintenance documents to include
new actions (e.g., inspections). Compliance
with these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these actions, the
operator may not be able to accomplish the
actions described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance (AMOC)
according to paragraph (m)(1) of this AD. The
request should include a description of
changes to the required inspections that will
Jkt 229001
(e) Reason
This AD was prompted by a new
modification developed to safeguard the
integrity of the MLG assembly and improve
surface protection of the affected area of the
MLG piston. We are issuing this AD to
prevent MLG failure, possibly resulting in
loss of control of the airplane during the
landing roll-out.
(g) Retained Initial Inspection
1. The authority citation for part 39
continues to read as follows:
13:24 Nov 14, 2012
Air Transport Association (ATA) of
America Code 32: Landing Gear.
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
■
VerDate Mar<15>2010
(d) Subject
(f) Compliance
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
ensure the continued operational safety of
the airplane.
This paragraph restates the initial
inspection required by paragraph (g) of AD
2011–04–01, Amendment 39–16601 (76 FR
8618, February 15, 2011). Within 30 days
after March 22, 2011 (the effective date of AD
2011–04–01), do a detailed visual inspection
for cracks of the MLG pistons, in accordance
with the Accomplishment Instructions of
Fokker Service Bulletin SBF100–32–158,
dated October 2, 2009.
(h) Retained Replacement
This paragraph restates the replacement
required by paragraph (h) of AD 2011–04–01,
Amendment 39–16601 (76 FR 8618, February
15, 2011). If any cracked MLG piston is found
during the inspection required by paragraph
(g) of this AD, before further flight, replace
the affected piston with a serviceable part, in
accordance with the Accomplishment
Instructions of Fokker Service Bulletin
SBF100–32–158, dated October 2, 2009.
(i) New Modification
Within 120 months, or during a scheduled
overhaul of the MLG, whichever occurs first
after the effective date of this AD: Modify the
MLG by installing a piston containing P/N
41141–5, in accordance with the
Accomplishment Instructions of Fokker
Service Bulletin SBF100–32–161, dated April
7, 2011. Re-installation of a MLG piston that
has been modified and re-identified as P/N
41141–5, in accordance with the
Accomplishment Instructions of Goodrich
Service Bulletin 41000–32–29, dated
November 10, 2010, is an optional method of
compliance for the requirements specified in
paragraph (i) of this AD. It is acceptable to
operate an airplane with one MLG having a
P/N 41141–5 piston installed, and the other
MLG having a P/N 41141–3 piston installed,
provided all MLG P/N 41141–3 are replaced
within the compliance times specified in
paragraph (i) of this AD.
(j) New Parts Installation Prohibition
After 120 months after the effective date of
this AD: No person may install a MLG piston,
P/N 41141–3, or a MLG unit equipped with
a MLG piston P/N 41141–3, on any airplane.
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(k) New Revision of the Airplane
Maintenance Program
Within 2 months after the effective date of
this AD: Revise the airplane maintenance
program by incorporating Task 321100–01–
16, Inspection of MLG Piston, and associated
thresholds and intervals described in Fokker
Report, SE–623, Fokker 70/100
Airworthiness Limitation Items and Safe Life
Items, Issue 8, dated December 20, 2010. The
initial compliance time for Task 321100–01–
16 is within 2 months after the effective date
of this AD.
(l) No Alternative Actions or Intervals
After accomplishing the revisions required
by paragraph (k) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used other than those specified in Fokker
Report, SE–623, Fokker 70/100
Airworthiness Limitation Items and Safe Life
Items, Issue 8, dated December 20, 2010,
unless the actions and intervals are approved
as an AMOC in accordance with the
procedures specified in paragraph (m)(1) of
this AD.
(m) Other FAA AD Provisions
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.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it 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. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding 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.
(n) Related Information
Refer to MCAI European Aviation Safety
Agency Airworthiness Directive 2011–0159,
dated August 26, 2011, and the service
information specified in paragraphs
(n)(1)through (n)(4) of this AD, for related
information.
(1) Fokker Service Bulletin SBF100–32–
158, dated October 2, 2009.
(2) Fokker Service Bulletin SBF100–32–
161, dated April 7, 2011.
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Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations
(3) Fokker Report, SE–623, Fokker 70/100
Airworthiness Limitation Items and Safe Life
Items, Issue 8, dated December 20, 2010.
(4) Goodrich Service Bulletin 41000–32–
29, dated November 10, 2010.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on December 20, 2012.
(i) Fokker Service Bulletin SBF100–32–
161, dated April 7, 2011.
(ii) Fokker Report, SE–623, Fokker 70/100
Airworthiness Limitation Items and Safe Life
Items, Issue 8, dated December 20, 2010.
(iii) Goodrich Service Bulletin 41000–32–
29, dated November 10, 2010.
(4) The following service information was
approved for IBR on March 22, 2011 (76 FR
8618, February 15, 2011).
(i) Fokker Service Bulletin SBF100–32–
158, dated October 2, 2009.
(ii) Reserved.
(5) 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; email
technicalservices.fokkerservices@stork.com;
Internet https://www.myfokkerfleet.com. For
Goodrich Corporation service information
identified in this AD, contact Goodrich, 1400
South Service Road, West Oakville, L6L 5Y7,
Ontario, Canada, telephone +1–905–827–
7777; fax +1–905–825–1583; Internet https://
www.goodrich.com/TechPubs.
(6) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(7) You may view this 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
wreier-aviles on DSK5TPTVN1PROD with
Issued in Renton, Washington, on October
24, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–26781 Filed 11–14–12; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
13:24 Nov 14, 2012
Jkt 229001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0530; Directorate
Identifier 2011–SW–075–AD; Amendment
39–17247; AD 2012–22–11]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Bell
Helicopter Textron (BHT) Model 412,
412EP, and 412CF helicopters. This AD
requires a repetitive inspection of the
collective lever for a crack, and if there
is a crack, before further flight, replacing
the collective lever with an airworthy
collective lever. This AD was prompted
by a reported failure of a collective
lever. The actions are intended to detect
a crack in the collective lever, which
could lead to failure of the collective
lever and subsequent loss of control of
the helicopter.
DATES: This AD is effective December
20, 2012.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of December 20, 2012.
ADDRESSES: For service information
identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482,
Fort Worth, Texas 76101; telephone
(817) 280–3391; fax (817) 280–6466; or
at https://www.bellcustomer.com/files/.
You may review a copy of the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas
76137.
Examining the AD Docket: You may
examine the AD docket on the Internet
at https://www.regulations.gov or in
person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
SUMMARY:
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
68055
FOR FURTHER INFORMATION CONTACT:
Martin Crane, Aerospace Engineer,
Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5170; email
martin.r.crane@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On May 22, 2012, at 77 FR 30232, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 to
include an AD that would apply to
certain serial-numbered BHT Model
412, 412EP, and 412CF helicopters with
a collective lever, part number (P/N)
412–010–408–101. That NPRM
proposed to require within 25 hours
time-in-service (TIS) or 30 days,
whichever occurs first, and thereafter at
intervals not to exceed 100 hours TIS,
cleaning the collective lever and
inspecting it for cracks with a 10X or
higher power magnifying glass. If there
is a crack in the collective lever paint
finish, the NPRM proposed to require
removing the collective lever from the
swashplate and performing a fluorescent
penetrant inspection, and if there is a
crack in the collective lever, before
further flight, replacing the collective
lever with an airworthy collective lever.
The proposed requirements were
intended to detect a crack in the
collective lever, which could lead to
failure of the collective lever and
subsequent loss of control of the
helicopter.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (77 FR 30232, May 22, 2012).
FAA’s Determination
We have reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other products of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed.
Related Service Information
We reviewed Bell Helicopter Alert
Service Bulletin (ASB) No. 412–11–148
and ASB No. 412CF–11–47, both
Revision A, and both dated December
12, 2011, which describe procedures for
repetitively inspecting the collective
lever with a magnifying glass and a
strong light source and, if necessary, a
fluorescent penetrant inspection. If
there is a crack, the ASBs require
replacing the collective lever.
E:\FR\FM\15NOR1.SGM
15NOR1
]]>Agencies
[Federal Register Volume 77, Number 221 (Thursday, November 15, 2012)]
[Rules and Regulations]
[Pages 68052-68055]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-26781]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0643; Directorate Identifier 2011-NM-190-AD;
Amendment 39-17241; AD 2012-22-05]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain Fokker Services B.V. Model F.28 Mark 0070 and 0100
airplanes. That AD currently requires performing a detailed visual
inspection for cracks of the pistons on the main landing gear (MLG),
and replacing the affected pistons if necessary. This new AD also
requires modifying the MLG by installing a piston containing a certain
part number, and revising the airplane maintenance program. This AD was
prompted by a new modification developed to safeguard the integrity of
the MLG assembly and improve surface protection of the affected area of
the MLG piston. We are issuing this AD to prevent MLG failure, possibly
resulting in loss of control of the airplane during the landing roll-
out.
DATES: This AD becomes effective December 20, 2012.
[[Page 68053]]
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 20,
2012.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of March
22, 2011 (76 FR 8618, February 15, 2011).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: 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 June 21, 2012 (77 FR
37337), and proposed to supersede AD 2011-04-01, Amendment 39-16601 (76
FR 8618, February 15, 2011). That NPRM proposed to correct an unsafe
condition for the specified products. The Mandatory Continuing
Airworthiness Information (MCAI) states:
During a normal walk around check on a F28 Mark 0100 aeroplane,
a large crack was discovered in the lower portion of the right (RH)
MLG piston. The affected MLG unit had accumulated 7,909 flight
cycles (FC) at the time of detection. The piston was sent to
Goodrich, the landing gear manufacturer, for detailed investigation,
which revealed that the crack had been initiated by corrosion pits.
The extent of the corrosion indicates that the initial crack existed
for a substantial period before a high loading event caused the
crack to grow further by ductile overload.
This condition, if not detected and corrected, could lead to MLG
failure during the landing roll-out, possibly resulting in damage to
the aeroplane and injury to occupants.
To address this potential unsafe condition, EASA [European
Aviation Safety Agency] issued AD 2009-0221 [which corresponds with
FAA AD 2011-04-01, Amendment 39-16601 (76 FR 8618, February 15,
2011)] to require a one-time detailed visual inspection of the MLG
pistons, the replacement of any MLG pistons on which cracks are
detected, and the reporting of all findings to the aeroplane TC
[type certificate] holder. No cracks were reported as a result of
this inspection.
Subsequently, a repetitive inspection was introduced in the
Airworthiness Limitations Section (Fokker Services report SE-623
Issue 8) in Appendix 1 of the Maintenance Review Board (MRB)
document to safeguard the integrity of the MLG assembly, pending the
accomplishment of a terminating action.
Goodrich issued Service Bulletin (SB) 41000-32-29 to introduce
an improved surface protection (nickel plate) of the affected area
of the MLG piston P/N [part number] 41141-3 and re-identification as
P/N 41141-5, which is considered as a terminating action for the
repetitive inspections.
For the reasons described above, this [EASA] AD requires
repetitive visual inspections of the P/N 41141-3 MLG piston for
cracks and, depending on findings, replacement or modification of
the MLG piston. This [EASA] AD also requires modification of the
affected MLG by installing a piston P/N 41141-5.
You may obtain further information by examining the MCAI in the AD
docket.
Change Made to This AD
We have revised paragraphs (k), (l), and (n), of this final rule to
clarify the document citation of Fokker Report SE-623 to meet the
Office of Federal Register's guidelines for materials incorporated by
reference. There is no change to the requirements specified in those
paragraphs.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (77 FR 37337, June 21,
2012) 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--except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 37337, June 21, 2012) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 37337, June 21, 2012).
Costs of Compliance
We estimate that this AD will affect about 2 products of U.S.
registry.
The actions that are required by AD 2011-04-01, Amendment 39-16601
(76 FR 8618, February 15, 2011), and retained in this AD take about 3
work-hours per product, at an average labor rate of $85 per work-hour.
Based on these figures, the estimated cost of the currently required
actions is $255 per product.
We estimate that it will take about 24 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD to the U.S. operators to be $4,080, or $2,040 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 that 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);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket
[[Page 68054]]
contains the NPRM (77 FR 37337, June 21, 2012), the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2011-04-01, Amendment 39-16601 (76 FR 8618, February 15, 2011), and
adding the following new AD:
2012-22-05 Fokker Services B.V.: Amendment 39-17241. Docket No. FAA-
2012-0643; Directorate Identifier 2011-NM-190-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective December 20,
2012.
(b) Affected ADs
This AD supersedes AD 2011-04-01, Amendment 39-16601 (76 FR
8618, February 15, 2011).
(c) Applicability
(1) This AD applies to Fokker Services B.V. Model F.28 Mark 0070
and 0100 airplanes, certificated in any category, all serial
numbers, equipped with Goodrich (formerly Menasco, Colt Industries)
main landing gear (MLG) units, part numbers (P/N) 41050-7, 41050-8,
41050-9, 41050-10, 41050-11, 41050-12, 41050-13, 41050-14, 41050-15,
41050-16, 41060-1, 41060-2, 41060-3, 41060-4, 41060-5, or 41060-6.
(2) This AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections). Compliance
with these inspections is required by 14 CFR 91.403(c). For
airplanes that have been previously modified, altered, or repaired
in the areas addressed by these actions, the operator may not be
able to accomplish the actions described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance (AMOC)
according to paragraph (m)(1) of this AD. The request should include
a description of changes to the required inspections that will
ensure the continued operational safety of the airplane.
(d) Subject
Air Transport Association (ATA) of America Code 32: Landing
Gear.
(e) Reason
This AD was prompted by a new modification developed to
safeguard the integrity of the MLG assembly and improve surface
protection of the affected area of the MLG piston. We are issuing
this AD to prevent MLG failure, possibly resulting in loss of
control of the airplane during the landing roll-out.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Initial Inspection
This paragraph restates the initial inspection required by
paragraph (g) of AD 2011-04-01, Amendment 39-16601 (76 FR 8618,
February 15, 2011). Within 30 days after March 22, 2011 (the
effective date of AD 2011-04-01), do a detailed visual inspection
for cracks of the MLG pistons, in accordance with the Accomplishment
Instructions of Fokker Service Bulletin SBF100-32-158, dated October
2, 2009.
(h) Retained Replacement
This paragraph restates the replacement required by paragraph
(h) of AD 2011-04-01, Amendment 39-16601 (76 FR 8618, February 15,
2011). If any cracked MLG piston is found during the inspection
required by paragraph (g) of this AD, before further flight, replace
the affected piston with a serviceable part, in accordance with the
Accomplishment Instructions of Fokker Service Bulletin SBF100-32-
158, dated October 2, 2009.
(i) New Modification
Within 120 months, or during a scheduled overhaul of the MLG,
whichever occurs first after the effective date of this AD: Modify
the MLG by installing a piston containing P/N 41141-5, in accordance
with the Accomplishment Instructions of Fokker Service Bulletin
SBF100-32-161, dated April 7, 2011. Re-installation of a MLG piston
that has been modified and re-identified as P/N 41141-5, in
accordance with the Accomplishment Instructions of Goodrich Service
Bulletin 41000-32-29, dated November 10, 2010, is an optional method
of compliance for the requirements specified in paragraph (i) of
this AD. It is acceptable to operate an airplane with one MLG having
a P/N 41141-5 piston installed, and the other MLG having a P/N
41141-3 piston installed, provided all MLG P/N 41141-3 are replaced
within the compliance times specified in paragraph (i) of this AD.
(j) New Parts Installation Prohibition
After 120 months after the effective date of this AD: No person
may install a MLG piston, P/N 41141-3, or a MLG unit equipped with a
MLG piston P/N 41141-3, on any airplane.
(k) New Revision of the Airplane Maintenance Program
Within 2 months after the effective date of this AD: Revise the
airplane maintenance program by incorporating Task 321100-01-16,
Inspection of MLG Piston, and associated thresholds and intervals
described in Fokker Report, SE-623, Fokker 70/100 Airworthiness
Limitation Items and Safe Life Items, Issue 8, dated December 20,
2010. The initial compliance time for Task 321100-01-16 is within 2
months after the effective date of this AD.
(l) No Alternative Actions or Intervals
After accomplishing the revisions required by paragraph (k) of
this AD, no alternative actions (e.g., inspections) or intervals may
be used other than those specified in Fokker Report, SE-623, Fokker
70/100 Airworthiness Limitation Items and Safe Life Items, Issue 8,
dated December 20, 2010, unless the actions and intervals are
approved as an AMOC in accordance with the procedures specified in
paragraph (m)(1) of this AD.
(m) Other FAA AD Provisions
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. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it 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.
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding 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.
(n) Related Information
Refer to MCAI European Aviation Safety Agency Airworthiness
Directive 2011-0159, dated August 26, 2011, and the service
information specified in paragraphs (n)(1)through (n)(4) of this AD,
for related information.
(1) Fokker Service Bulletin SBF100-32-158, dated October 2,
2009.
(2) Fokker Service Bulletin SBF100-32-161, dated April 7, 2011.
[[Page 68055]]
(3) Fokker Report, SE-623, Fokker 70/100 Airworthiness
Limitation Items and Safe Life Items, Issue 8, dated December 20,
2010.
(4) Goodrich Service Bulletin 41000-32-29, dated November 10,
2010.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
December 20, 2012.
(i) Fokker Service Bulletin SBF100-32-161, dated April 7, 2011.
(ii) Fokker Report, SE-623, Fokker 70/100 Airworthiness
Limitation Items and Safe Life Items, Issue 8, dated December 20,
2010.
(iii) Goodrich Service Bulletin 41000-32-29, dated November 10,
2010.
(4) The following service information was approved for IBR on
March 22, 2011 (76 FR 8618, February 15, 2011).
(i) Fokker Service Bulletin SBF100-32-158, dated October 2,
2009.
(ii) Reserved.
(5) 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; email
technicalservices.fokkerservices@stork.com; Internet https://www.myfokkerfleet.com. For Goodrich Corporation service information
identified in this AD, contact Goodrich, 1400 South Service Road,
West Oakville, L6L 5Y7, Ontario, Canada, telephone +1-905-827-7777;
fax +1-905-825-1583; Internet https://www.goodrich.com/TechPubs.
(6) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
(7) You may view this 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on October 24, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-26781 Filed 11-14-12; 8:45 am]
BILLING CODE 4910-13-P
