Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes, 64633-64636 [2010-26224]
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Federal Register / Vol. 75, No. 202 / Wednesday, October 20, 2010 / Rules and Regulations
electric furnaces and boilers, BOH =
100(2080)(0.77)DHR/(Ein 3.412)(AFUE))
Where:
100 = to express a percent as a decimal
2,080 = as specified in 10.2.1 of this
appendix
0.77 = as specified in 10.2.1 of this appendix
DHR = as defined in 10.2.1 of this appendix
3.412 = conversion to express energy in terms
of KBtu instead of kilowatt-hours
AFUE = as defined in 11.1 of ANSI/ASHRAE
Standard 103—1993 (incorporated by
reference, see § 430.3) in percent
E in = Steady-state electric rated power, in
kilowatts, from section 9.3 of ANSI/
ASHRAE Standard 103—1993
(incorporated by reference, see § 430.3).
[FR Doc. 2010–26369 Filed 10–19–10; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1036; Directorate
Identifier 2009–NM–247–AD; Amendment
39–16480; AD 2010–22–01]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 767–200, –300, and
–300F Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
the products listed above. That AD
currently requires repetitive inspections
for fatigue cracking and corrosion of the
upper link fuse pin of the nacelle struts,
and related investigative and corrective
actions if necessary. The existing AD
also provides terminating action for the
repetitive inspections. This AD revises
certain criteria for the terminating
action. This AD was prompted by two
reports of cracked upper link fuse pins.
We are issuing this AD to prevent
fatigue cracking or corrosion of the
upper link fuse pin, which could result
in failure of the fuse pin and consequent
reduced structural integrity of the
nacelle strut and possible separation of
the strut and engine from the airplane
during flight.
DATES: This AD is effective November 4,
2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 4, 2010.
The Director of the Federal Register
approved the incorporation by reference
emcdonald on DSK2BSOYB1PROD with RULES
SUMMARY:
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of a certain other publication listed in
this AD as of November 5, 2009 (74 FR
50692, October 1, 2009).
We must receive comments on this
AD by December 6, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. 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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6577; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
On September 18, 2009, we issued AD
2009–20–09, Amendment 39–16032 (74
FR 50692, October 1, 2009), for certain
Model 767–200, –300, and –300F series
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64633
airplanes. That AD requires repetitive
inspections for fatigue cracking and
corrosion of the upper link fuse pin of
the nacelle struts, and related
investigative and corrective actions if
necessary. That AD also provides
terminating action for the repetitive
inspections. That AD resulted from two
reports of cracked upper link fuse pins.
We issued that AD to prevent fatigue
cracking or corrosion of the upper link
fuse pin, which could result in failure
of the fuse pin and consequent reduced
structural integrity of the nacelle strut
and possible separation of the strut and
engine from the airplane during flight.
Actions Since Existing AD Was Issued
We have learned that paragraph (h) of
AD 2009–20–09 incorrectly identifies
the pin replacement as acceptable for
compliance with the optional strut
modification specified in paragraph (g)
of that AD. Rather, replacing the pin
terminates only the repetitive
inspections of the pins as required by
paragraph (g) of this AD; replacing the
pin does not terminate the requirement
for the strut modification. We have
removed credit for replacement of the
fuse pins with new fuse pins from
paragraph (h) of the existing AD
(specified as paragraph (i) in this AD)
because it is not a terminating action.
We have added new paragraph (j) in this
AD to specify that replacement of the
fuse pins terminates the repetitive
inspection requirements of paragraph (g)
of this AD, and the strut modification is
still required.
We have also revised paragraph (b) of
this AD to clarify that certain
requirements of this AD terminate
certain requirements of AD 2000–19–09,
Amendment 39–11910 (65 FR 58641,
October 2, 2000), and AD 2004–16–12,
Amendment 39–13768 (69 FR 51002,
August 17, 2004).
Explanation of Additional Paragraph in
the AD
We have added a new paragraph (d)
to this AD to provide the Air Transport
Association (ATA) of America subject
code 54: Nacelles/Pylons. This code is
added to make this AD parallel with
other new AD actions. We have
reidentified subsequent paragraphs
accordingly.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of these same
type designs.
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64634
Federal Register / Vol. 75, No. 202 / Wednesday, October 20, 2010 / Rules and Regulations
AD Requirements
This AD requires repetitive
inspections for fatigue cracking and
corrosion of the upper link fuse pin of
the nacelle struts, and related
investigative and corrective actions if
necessary. This AD also provides
terminating action for the repetitive
inspections.
FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because this AD shortens the time
for the repetitive intervals. Therefore,
we find that notice and opportunity for
prior public comment are impracticable
and that good cause exists for making
this amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2010–1036; Directorate Identifier 2009–
NM–247–AD;’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Costs of Compliance
We estimate that this AD affects 354
airplanes of U.S. registry. This new AD
adds no new costs to affected operators.
The current costs for this AD are
repeated for the convenience of affected
operators, as follows:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Inspection of fuse pins (requirement of AD 2009–20–
09).
4 work-hours × $85 per hour
= $340 per inspection cycle.
$0
Cost per product
Cost on U.S. operators
$340 per inspection cycle .....
$120,360 per inspection cycle.
emcdonald on DSK2BSOYB1PROD with RULES
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.
(2) Is not a ‘‘significant rule’’ under
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.
Effective Date
List of Subjects in 14 CFR Part 39
(c) This AD applies to The Boeing
Company Model 767–200, –300, and –300F
series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin
767–54A0074, Revision 1, dated April 24,
2008.
Regulatory Findings
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,
■
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Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
(a) This AD is effective November 4, 2010.
Affected ADs
(b) This AD supersedes AD 2009–20–09,
Amendment 39–16032. Certain requirements
of this AD terminate certain requirements of
AD 2000–19–09, Amendment 39–11910, and
AD 2004–16–12, Amendment 39–13768.
Applicability
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
Subject
PART 39—AIRWORTHINESS
DIRECTIVES
Unsafe Condition
■
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
The FAA amends § 39.13 by removing
airworthiness directive (AD) 2009–20–
09, Amendment 39–16032 (74 FR
50692, October 1, 2009), and adding the
following new AD:
■
2010–22–01 The Boeing Company:
Amendment 39–16480; Docket No.
FAA–2010–1036; Directorate Identifier
2009–NM–247–AD.
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(d) Joint Aircraft System Component
(JASC)/Air Transport Association (ATA) of
America Code 54: Nacelles/Pylons.
(e) This AD was prompted by two reports
of cracked upper link fuse pins. We are
issuing this AD to prevent fatigue cracking or
corrosion of the upper link fuse pin, which
could result in failure of the fuse pin and
consequent reduced structural integrity of the
nacelle strut and possible separation of the
strut and engine from the airplane during
flight.
Compliance
(f) Comply with this AD within the
compliance times specified, unless already
done.
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Federal Register / Vol. 75, No. 202 / Wednesday, October 20, 2010 / Rules and Regulations
Restatement of Requirements of AD 2009–
20–09, With Revised Credit Provisions in
Paragraph (I) of This AD
Initial and Repetitive Inspections/
Investigative and Corrective Actions
(g) Inspect the upper link fuse pin of the
nacelle struts for fatigue cracking and
corrosion at the applicable time specified in
Table 1 of this AD. Do the applicable
inspection by doing all the applicable actions
specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–54A0074, Revision 1, dated April 24,
2008; and do all applicable related
investigative and corrective actions before
64635
further flight. Repeat the applicable
inspection at intervals not to exceed 3,000
flight cycles or 24 months, whichever is first,
until the requirements of paragraph (h) of
this AD have been done.
TABLE 1—COMPLIANCE TIMES
At the later of:
Engine type
Initial inspection threshold
Grace period
JT9D ..................
14,000 total flight cycles ..........................
CF6–80A ...........
PW4000 .............
CF6–80C2 .........
RB211 ................
24,000 total flight cycles ..........................
8,000 total flight cycles ............................
10,000 total flight cycles ..........................
24,000 total flight cycles ..........................
Within 3,000 flight cycles or 18 months after November 5, 2009 (the effective
date of AD 2009-20–09), whichever is first.
Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first.
Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first.
Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first.
Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first.
Note 1: The upper link inspections can be
done with the pylon and/or engine in any
position.
Note 2: In paragraph 3.B, Steps 4.b.(1)(a)
and 4.b.(2)(b)(2){a} of the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–54A0074, Revision 1, dated April 24,
2008, the procedures specify to apply two
layers of Boeing Material Specification (BMS)
10–11 primer to the inside surface of the fuse
pin if no crack indication is found. However,
two layers of primer are only necessary to
touch up bare areas on the fuse pin if no
crack indication is found.
emcdonald on DSK2BSOYB1PROD with RULES
Terminating Action in AD 2000–19–09,
Amendment 39–11910, and AD 2004–16–12,
Amendment 39–13768
(h) Accomplishment of the modification
specified in paragraph (h)(1) or (h)(2) of this
AD, as applicable, terminates the inspections
required by paragraph (g) of this AD.
(1) For Model 767 series airplanes powered
by Rolls-Royce RB211 series engines, as
identified in AD 2000–19–09: Modification of
the nacelle strut and wing structure, as
required by paragraphs (a) and (b) of AD
2000–19–09.
(2) For Model 767–200, –300, and –300F
series airplanes powered by Pratt & Whitney
and General Electric engines, as identified in
AD 2004–16–12: Modification of the nacelle
strut and wing structure, as required by
paragraphs (a), (b), (d), and (e) of AD 2004–
16–12.
Credit for Inspection Done Using Previous
Service Information
(i) Inspection of the fuse pins before
November 5, 2009, in accordance with
Boeing Service Bulletin 767–54–0074, dated
March 27, 1997, is acceptable for compliance
with the inspections required by paragraph
(g) of this AD, except that operator’s
equivalent procedures are not allowed.
New Requirements of This AD
Optional Terminating Action for Inspections
(j) Replacement of the fuse pins with new
fuse pins (not serviceable fuse pins), in
accordance with Boeing Service Bulletin
767–54–0074, dated March 27, 1997; or
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16:03 Oct 19, 2010
Jkt 223001
Boeing Alert Service Bulletin 767–54A0074,
Revision 1, dated April 24, 2008; terminates
the repetitive inspections of the fuse pins
required by paragraph (g) of this AD.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your Principal Maintenance Inspector
or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
to make those findings. For a repair method
to be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
AMOCs that specified using new pins (not
serviceable pins) approved previously in
accordance with AD 2009–20–09,
Amendment 39–16032, are approved as
AMOCs for the corresponding provisions of
paragraph (h) of this AD.
Related Information
(l) For more information about this AD,
contact Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6577; fax (425)
917–6590.
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Material Incorporated by Reference
(m) You must use Boeing Alert Service
Bulletin 767–54A0074, Revision 1, dated
April 24, 2008, to do the actions required by
this AD, unless the AD specifies otherwise.
If you accomplish the optional terminating
actions specified in this AD, you must use
Boeing Alert Service Bulletin 767–54A0074,
Revision 1, dated April 24, 2008; or Boeing
Service Bulletin 767–54–0074, dated March
27, 1997; to perform those actions, unless the
AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Service Bulletin 767–54–0074, dated
March 27, 1997, under 5 U.S.C. 552(a) and
1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Boeing Alert Service Bulletin
767–54A0074, Revision 1, dated April 24,
2008, on November 5, 2009 (74 FR 50692,
October 1, 2009).
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(4) 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.
(5) 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 an NARA facility, call 202–741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
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Federal Register / Vol. 75, No. 202 / Wednesday, October 20, 2010 / Rules and Regulations
Issued in Renton, Washington, on October
6, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–26224 Filed 10–19–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1037; Directorate
Identifier 2010–NM–202–AD; Amendment
39–16481; AD 2010–22–02]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Model CL–600–2B19 (Regional Jet
Series 100 & 440) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
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:
SUMMARY:
Seven cases of on-ground hydraulic
accumulator screw cap/end cap failure have
been experienced on CL–600–2B19
aeroplanes, resulting in the loss of the
associated hydraulic system and high-energy
impact damage to adjacent systems and
structure. * * *
*
*
*
*
*
A detailed analysis of the calculated line
of trajectory of a failed screw cap/end cap for
each of the accumulators has been
conducted, resulting in the identification of
several areas where systems and/or structural
components could potentially be damaged.
Although all of the failures to date have
occurred on the ground, an in-flight failure
affecting such components could potentially
have an adverse effect on the controllability
of the aeroplane.
emcdonald on DSK2BSOYB1PROD with RULES
*
*
*
*
*
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
This AD becomes effective
November 4, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of November 4, 2010.
We must receive comments on this
AD by December 6, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
DATES:
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, 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.
FOR FURTHER INFORMATION CONTACT:
Christopher Alfano, Aerospace
Engineer, Airframe and Mechanical
Systems Branch, ANE–171, FAA, New
York Aircraft Certification Office (ACO),
1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone
(516) 228–7340; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2010–24,
dated August 3, 2010 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Seven cases of on-ground hydraulic
accumulator screw cap/end cap failure have
been experienced on CL–600–2B19
aeroplanes, resulting in the loss of the
associated hydraulic system and high-energy
impact damage to adjacent systems and
structure. The lowest number of flight cycles
accumulated at the time of failure, to date,
has been 6,991 flight cycles.
The part numbers (P/N) of the
accumulators currently installed on CL–600–
2B19 aeroplanes are 601R75138–1 (08–
60163–001 or 08–60163–002) [Hydraulic
System No. 1, Hydraulic System No. 2,
Inboard Brake and Outboard Brake
accumulators] and 601R75138–3 (08–60164–
001 or 08–60164–002) [Hydraulic System No.
3 accumulator].
A detailed analysis of the calculated line
of trajectory of a failed screw cap/end cap for
each of the accumulators has been
conducted, resulting in the identification of
several areas where systems and/or structural
components could potentially be damaged.
Although all of the failures to date have
occurred on the ground, an in-flight failure
affecting such components could potentially
have an adverse effect on the controllability
of the aeroplane.
This directive gives instructions to amend
the Airplane Flight Manual (AFM), remove
two accumulators (Hydraulic System No. 2
and No. 3) from the aeroplane and conduct
repetitive ultrasonic inspections [for cracks]
of the Hydraulic System No. 1, Inboard Brake
and Outboard Brake accumulators that are
not identified by the letter ‘‘T’’ after the serial
number (S/N) on the identification plate for
cracks until they are replaced by new
accumulators P/N 601R75139–1 (11093–4).
Required actions also include
deactivating the hydraulic system No. 3
accumulator. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Bombardier has issued Canadair
Regional Jet Temporary Revision (TR)
RJ/186–1, dated August 24, 2010, to the
Limitations section, Normal Procedures
section, and Abnormal Procedures
section of the Canadair Regional Jet
Airplane Flight Manual (AFM), CSP A–
012. Canadair Regional Jet TR RJ/186–1,
dated August 24, 2010, advises the
flightcrew that for certain airplanes the
hydraulic 3B pump is selected ‘‘on’’
instead of ‘‘auto’’ for all phases of flight.
Bombardier has issued the service
information in the following table:
BOMBARDIER SERVICE BULLETINS
Document
Revision
Bombardier Alert Service Bulletin A601R–29–029, including Appendix A, dated October 18,
2007.
Bombardier Alert Service Bulletin A601R–29–031 .........................................................................
B ................................
May 11, 2010.
A ................................
March 26, 2009.
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Date
]]>Agencies
[Federal Register Volume 75, Number 202 (Wednesday, October 20, 2010)]
[Rules and Regulations]
[Pages 64633-64636]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-26224]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1036; Directorate Identifier 2009-NM-247-AD;
Amendment 39-16480; AD 2010-22-01]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 767-200, -300,
and -300F Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. That AD currently requires repetitive
inspections for fatigue cracking and corrosion of the upper link fuse
pin of the nacelle struts, and related investigative and corrective
actions if necessary. The existing AD also provides terminating action
for the repetitive inspections. This AD revises certain criteria for
the terminating action. This AD was prompted by two reports of cracked
upper link fuse pins. We are issuing this AD to prevent fatigue
cracking or corrosion of the upper link fuse pin, which could result in
failure of the fuse pin and consequent reduced structural integrity of
the nacelle strut and possible separation of the strut and engine from
the airplane during flight.
DATES: This AD is effective November 4, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 4,
2010.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 5, 2009 (74 FR 50692, October 1, 2009).
We must receive comments on this AD by December 6, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data & Services Management, P.O. Box
3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000,
extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6577; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
On September 18, 2009, we issued AD 2009-20-09, Amendment 39-16032
(74 FR 50692, October 1, 2009), for certain Model 767-200, -300, and -
300F series airplanes. That AD requires repetitive inspections for
fatigue cracking and corrosion of the upper link fuse pin of the
nacelle struts, and related investigative and corrective actions if
necessary. That AD also provides terminating action for the repetitive
inspections. That AD resulted from two reports of cracked upper link
fuse pins. We issued that AD to prevent fatigue cracking or corrosion
of the upper link fuse pin, which could result in failure of the fuse
pin and consequent reduced structural integrity of the nacelle strut
and possible separation of the strut and engine from the airplane
during flight.
Actions Since Existing AD Was Issued
We have learned that paragraph (h) of AD 2009-20-09 incorrectly
identifies the pin replacement as acceptable for compliance with the
optional strut modification specified in paragraph (g) of that AD.
Rather, replacing the pin terminates only the repetitive inspections of
the pins as required by paragraph (g) of this AD; replacing the pin
does not terminate the requirement for the strut modification. We have
removed credit for replacement of the fuse pins with new fuse pins from
paragraph (h) of the existing AD (specified as paragraph (i) in this
AD) because it is not a terminating action. We have added new paragraph
(j) in this AD to specify that replacement of the fuse pins terminates
the repetitive inspection requirements of paragraph (g) of this AD, and
the strut modification is still required.
We have also revised paragraph (b) of this AD to clarify that
certain requirements of this AD terminate certain requirements of AD
2000-19-09, Amendment 39-11910 (65 FR 58641, October 2, 2000), and AD
2004-16-12, Amendment 39-13768 (69 FR 51002, August 17, 2004).
Explanation of Additional Paragraph in the AD
We have added a new paragraph (d) to this AD to provide the Air
Transport Association (ATA) of America subject code 54: Nacelles/
Pylons. This code is added to make this AD parallel with other new AD
actions. We have reidentified subsequent paragraphs accordingly.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
[[Page 64634]]
AD Requirements
This AD requires repetitive inspections for fatigue cracking and
corrosion of the upper link fuse pin of the nacelle struts, and related
investigative and corrective actions if necessary. This AD also
provides terminating action for the repetitive inspections.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because this
AD shortens the time for the repetitive intervals. Therefore, we find
that notice and opportunity for prior public comment are impracticable
and that good cause exists for making this amendment effective in less
than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2010-1036; Directorate
Identifier 2009-NM-247-AD;'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 354 airplanes of U.S. registry.
This new AD adds no new costs to affected operators. The current costs
for this AD are repeated for the convenience of affected operators, as
follows:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Inspection of fuse pins (requirement 4 work-hours x $85 per $0 $340 per inspection $120,360 per inspection cycle.
of AD 2009-20-09). hour = $340 per cycle.
inspection cycle.
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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
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 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.
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
The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2009-20-09, Amendment 39-16032 (74 FR 50692, October 1, 2009), and
adding the following new AD:
2010-22-01 The Boeing Company: Amendment 39-16480; Docket No. FAA-
2010-1036; Directorate Identifier 2009-NM-247-AD.
Effective Date
(a) This AD is effective November 4, 2010.
Affected ADs
(b) This AD supersedes AD 2009-20-09, Amendment 39-16032.
Certain requirements of this AD terminate certain requirements of AD
2000-19-09, Amendment 39-11910, and AD 2004-16-12, Amendment 39-
13768.
Applicability
(c) This AD applies to The Boeing Company Model 767-200, -300,
and -300F series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 767-54A0074, Revision 1,
dated April 24, 2008.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 54: Nacelles/Pylons.
Unsafe Condition
(e) This AD was prompted by two reports of cracked upper link
fuse pins. We are issuing this AD to prevent fatigue cracking or
corrosion of the upper link fuse pin, which could result in failure
of the fuse pin and consequent reduced structural integrity of the
nacelle strut and possible separation of the strut and engine from
the airplane during flight.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
[[Page 64635]]
Restatement of Requirements of AD 2009-20-09, With Revised Credit
Provisions in Paragraph (I) of This AD
Initial and Repetitive Inspections/Investigative and Corrective
Actions
(g) Inspect the upper link fuse pin of the nacelle struts for
fatigue cracking and corrosion at the applicable time specified in
Table 1 of this AD. Do the applicable inspection by doing all the
applicable actions specified in the Accomplishment Instructions of
Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April
24, 2008; and do all applicable related investigative and corrective
actions before further flight. Repeat the applicable inspection at
intervals not to exceed 3,000 flight cycles or 24 months, whichever
is first, until the requirements of paragraph (h) of this AD have
been done.
Table 1--Compliance Times
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At the later of:
----------------------------------------------
Engine type Initial inspection
threshold Grace period
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JT9D..................... 14,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009
(the effective date of
AD 2009[dash]20-09),
whichever is first.
CF6-80A.................. 24,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009,
whichever is first.
PW4000................... 8,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009,
whichever is first.
CF6-80C2................. 10,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009,
whichever is first.
RB211.................... 24,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009,
whichever is first.
------------------------------------------------------------------------
Note 1: The upper link inspections can be done with the pylon
and/or engine in any position.
Note 2: In paragraph 3.B, Steps 4.b.(1)(a) and
4.b.(2)(b)(2){a{time} of the Accomplishment Instructions of Boeing
Alert Service Bulletin 767-54A0074, Revision 1, dated April 24,
2008, the procedures specify to apply two layers of Boeing Material
Specification (BMS) 10-11 primer to the inside surface of the fuse
pin if no crack indication is found. However, two layers of primer
are only necessary to touch up bare areas on the fuse pin if no
crack indication is found.
Terminating Action in AD 2000-19-09, Amendment 39-11910, and AD 2004-
16-12, Amendment 39-13768
(h) Accomplishment of the modification specified in paragraph
(h)(1) or (h)(2) of this AD, as applicable, terminates the
inspections required by paragraph (g) of this AD.
(1) For Model 767 series airplanes powered by Rolls-Royce RB211
series engines, as identified in AD 2000-19-09: Modification of the
nacelle strut and wing structure, as required by paragraphs (a) and
(b) of AD 2000-19-09.
(2) For Model 767-200, -300, and -300F series airplanes powered
by Pratt & Whitney and General Electric engines, as identified in AD
2004-16-12: Modification of the nacelle strut and wing structure, as
required by paragraphs (a), (b), (d), and (e) of AD 2004-16-12.
Credit for Inspection Done Using Previous Service Information
(i) Inspection of the fuse pins before November 5, 2009, in
accordance with Boeing Service Bulletin 767-54-0074, dated March 27,
1997, is acceptable for compliance with the inspections required by
paragraph (g) of this AD, except that operator's equivalent
procedures are not allowed.
New Requirements of This AD
Optional Terminating Action for Inspections
(j) Replacement of the fuse pins with new fuse pins (not
serviceable fuse pins), in accordance with Boeing Service Bulletin
767-54-0074, dated March 27, 1997; or Boeing Alert Service Bulletin
767-54A0074, Revision 1, dated April 24, 2008; terminates the
repetitive inspections of the fuse pins required by paragraph (g) of
this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
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 manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your Principal
Maintenance Inspector or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector, your local Flight
Standards District Office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD. AMOCs that specified using new pins
(not serviceable pins) approved previously in accordance with AD
2009-20-09, Amendment 39-16032, are approved as AMOCs for the
corresponding provisions of paragraph (h) of this AD.
Related Information
(l) For more information about this AD, contact Berhane Alazar,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6577; fax (425) 917-6590.
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin 767-54A0074,
Revision 1, dated April 24, 2008, to do the actions required by this
AD, unless the AD specifies otherwise. If you accomplish the
optional terminating actions specified in this AD, you must use
Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April
24, 2008; or Boeing Service Bulletin 767-54-0074, dated March 27,
1997; to perform those actions, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Service Bulletin 767-54-0074,
dated March 27, 1997, under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Boeing Alert Service Bulletin 767-
54A0074, Revision 1, dated April 24, 2008, on November 5, 2009 (74
FR 50692, October 1, 2009).
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(4) 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.
(5) 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 an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
[[Page 64636]]
Issued in Renton, Washington, on October 6, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-26224 Filed 10-19-10; 8:45 am]
BILLING CODE 4910-13-P
