Airworthiness Directives; The Boeing Company Airplanes, 14987-14992 [2014-04843]
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Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations
Service Bulletin 757–54–0028, dated March
31, 1994, which is not incorporated by
reference in this AD.
(n) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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
paragraph (o)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) 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.
(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.
(4) AMOCs approved for AD 2004–12–07,
Amendment 39–13666 (69 FR 33561, June
16, 2004), are approved as AMOCs for
paragraphs (g) and (h) of this AD, except for
AMOCs that approved a revised compliance
time.
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(o) Related Information
(1) For more information about this AD,
contact Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, Seattle
Aircraft Certification Office (ACO), FAA,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6440; fax: 425–917–
6590; email: Nancy.Marsh@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the addresses specified in
paragraphs (p)(6) and (p)(7) of this AD.
(p) 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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on April 22, 2014.
(i) Boeing Service Bulletin 757–54–0003,
Revision 1, dated August 30, 1985.
(ii) Boeing Service Bulletin 757–54–0028,
Revision 1, dated August 25, 1994.
(iii) Boeing Service Bulletin 757–54–0035,
Revision 6, dated December 2, 2011.
(4) The following service information was
approved for IBR on July 21, 2004 (69 FR
33561, June 16, 2004).
(i) Boeing Service Bulletin 757–54–0035,
Revision 1, dated April 15, 1999.
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(ii) Boeing Service Bulletin 757–54–0035,
Revision 2, dated June 13, 2002.
(5) The following service information was
approved for IBR on January 3, 2000 (64 FR
66370, November 26, 1999).
(i) Boeing Service Bulletin 757–54–0035,
dated July 17, 1997.
(ii) Reserved.
(6) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; phone: 206–544–
5000, extension 1; fax: 206–766–5680;
Internet: https://www.myboeingfleet.com.
(7) You may view copies of this 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.
(8) 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 February
19, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–04826 Filed 3–17–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0369; Directorate
Identifier 2012–NM–128–AD; Amendment
39–17793; AD 2014–05–20]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 757 airplanes.
This AD was prompted by reports of
fractured rudder pedal pushrod
connecting bolts in a rudder pedal
assembly. This AD requires repetitive
replacements of the rudder pedal
pushrod connecting bolts and repetitive
inspections of the rudder pedal
assembly bolt holes in each of the
captain and the first officer rudder pedal
assemblies, and if necessary, repair or
replacement of worn rudder pedal
assemblies. We are issuing this AD to
prevent fracture of the rudder pedal
pushrod connecting bolts during pedal
SUMMARY:
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14987
use, which could result in large
involuntary inputs to the rudder and
nose-wheel steering and an asymmetric
application of braking, if pedal brakes
are applied, leading to a runway
excursion.
DATES: This AD is effective April 22,
2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of April 22, 2014.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356. 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 by searching for
and locating Docket No. FAA–2013–
0369; 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 address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, Seattle Aircraft Certification
Office, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–
917–6418; fax: 425–917–6590; email:
marie.hogestad@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all The Boeing Company Model
757 airplanes. The NPRM published in
the Federal Register on May 10, 2013
(78 FR 27315). The NPRM was
prompted by reports of fractured rudder
pedal pushrod connecting bolts in a
rudder pedal assembly. The NPRM
proposed to require repetitive
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Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations
replacements of the rudder pedal
pushrod connecting bolts and repetitive
inspections of the rudder pedal
assembly bolt holes in each of the
captain and the first officer rudder pedal
assemblies, and if necessary, repair or
replacement of worn rudder pedal
assemblies. We are issuing this AD to
prevent fracture of the rudder pedal
pushrod connecting bolts during pedal
use, which could result in large
involuntary inputs to the rudder and
nose-wheel steering and an asymmetric
application of braking, if pedal brakes
are applied, leading to a runway
excursion.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (78 FR 27315,
May 10, 2013) and the FAA’s response
to each comment.
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Request To Reduce the Compliance
Time
Air Line Pilots Association
International (the commenter) stated
that it agrees with the intent of the
NPRM (78 FR 27315, May 10, 2013), but
requested that we reduce the
compliance time from 60 months to 24
months. The commenter provided no
justification for this request.
We disagree with the request to revise
the compliance time in this final rule.
In developing the compliance time for
this final rule, we considered not only
the safety implications of the identified
unsafe condition, but also the average
utilization rate of the affected fleet, the
practical aspects of an orderly
modification of the fleet, the availability
of required parts, and the time necessary
for the rulemaking process. We find that
the compliance time, as proposed,
adequately represents an appropriate
interval of time in which the required
actions can be performed in a timely
manner within the affected fleet, while
still maintaining an adequate level of
safety. We have not changed this final
rule in this regard.
Request To Clarify the Unsafe
Condition
Boeing requested that we revise the
unsafe condition in the NPRM (78 FR
27315, May 10, 2013), and suggested
language to clarify the expectation of
asymmetric braking, in the event of
fracture of the subject bolt. Boeing
added that symmetric braking inputs
prior to fracture can become asymmetric
following bolt fracture due to loss of
brake inputs on the affected side.
We agree with the request to revise
the unsafe condition for the reasons
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provided by Boeing. We have revised
this final rule to reflect the revised
language.
Request To Use One Service Bulletin
Revision
Aviation Technical Services, Inc. (the
commenter) requested that we revise the
NPRM (78 FR 27315, May 10, 2013) to
mandate only one version of the service
information. The commenter also
requested that we require that Boeing
combine both versions of the service
bulletin specified in the NPRM, into one
final revision. The commenter reasoned
that having two versions of the service
bulletin will require operators and
maintenance providers to integrate the
two service bulletins in order to comply
with the NPRM. The commenter
expressed that this burden should be on
the original equipment manufacturer
(OEM) and the FAA.
The commenter also requested that to
further determine the adequacy of
Boeing Alert Service Bulletin 757–
27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29,
2012, the FAA should use its own
guidance, as provided by FAA Advisory
Circular (AC) 20–176, dated December
19, 2011 (https://rgl.avs.faa.gov/
Regulatory_and_Guidance_Library/
rgAdvisoryCircular.nsf/0/
a78cc91a47b192278625796b0075f419/
$FILE/AC%2020-176.pdf).
We disagree with the request to
provide a single service bulletin version
for the required method of compliance.
Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29,
2012, includes only minor corrections to
washer part numbers in top kit
012N8932–21 and an additional
instruction for getting better access, if
necessary, for the detailed inspections
required by this final rule. It is not
necessary that Boeing combine both
revisions of the referenced service
bulletin into one final revision.
Also, the design approval holder
(DAH) followed the guidance in FAA
AC 20–176, dated December 19, 2011
(https://rgl.avs.faa.gov/Regulatory_and_
Guidance_Library/
rgAdvisoryCircular.nsf/0/
a78cc91a47b192278625796b0075f419/
$FILE/AC%2020-176.pdf). We approved
Boeing Alert Service Bulletin 757–
27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29,
2012, using the guidance in FAA Order
8110.117, dated September 12, 2012
(https://rgl.avs.faa.gov/Regulatory_and_
Guidance_Library/rgOrders.nsf/0/
984bb9eb07cdd86986257a7f0070744c/
$FILE/Order%208110.117.pdf). (Refer to
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Section 2–11, ‘‘Streamlining
Development and Revision of SBs,’’
paragraph (c)(5), ‘‘Partial Revision
Process—A process in which only
changed information in a service
bulletin is sent to affected customers,’’
of FAA AC 20–176, dated December 19,
2011.) We have not changed this final
rule in this regard.
Request for Additional Guidance
Aviation Technical Services, Inc. (the
commenter) requested that we revise the
NPRM (78 FR 27315, May 10, 2013) to
provide sufficient instruction to
determine the installation finish
associated with the replacement
bushing for the rudder pedal pushrod.
The commenter reasoned that the
instructions provided by Boeing Alert
Service Bulletin 757–27A0153, dated
May 9, 2012, as revised by Boeing Alert
Service Bulletin 757–27A0153, Revision
1, dated October 29, 2012, refer to
Boeing Standard Overhaul Practices
Manual (SOPM) 20–50–03 for the shrink
fit procedure to install repair bushings,
and that the SOPM procedure contain
instructions such as: ‘‘Apply the
specified installation finish. . . .’’ and
‘‘Refer to the overhaul instructions for
applicable operations. . . .’’ The
commenter asserted that neither Boeing
Alert Service Bulletin 757–27A0153,
dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757–27A0153,
Revision 1, dated October 29, 2012, nor
the SOPM provide sufficient instruction
to determine the installation finish
associated with the replacement
bushing for the rudder pedal pushrod.
We disagree to revise this final rule.
Step 4 of Figures 3 and 4 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 757–27A0153,
dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757–27A0153,
Revision 1, dated October 29, 2012,
already provides procedures for
installing bushing 001N0004–1 with
BMS 5–95 sealant, as specified in ‘‘the
shrink fit’’ procedure referred to in
Standard Overhaul Practices Manual
(SOPM) 20–50–03 (bushing 001N0004–
1 is already finished). SOPM 20–50–03
Bearing and Bushing Replacement,
Paragraph 7.B, ‘‘Shrink Fit (Temperature
Differential) Procedure,’’ specifies,
among other things, to apply the
specified installation finish ‘‘as
specified in Paragraph 6B,’’ which, in
turn, specifies ‘‘Installation with
sealant.’’ The finish is, in this case, the
sealant that is used during the
installation (BMS 5–95). Therefore,
Boeing Alert Service Bulletin 757–
27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29,
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2012, in combination with SOPM 20–
50–03, provide sufficient instructions to
install the bushing. We have not
changed the AD in this regard.
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Request To Match Terminology
American Airlines (AAL) requested
that we revise the NPRM (78 FR 27315,
May 10, 2013) to match certain wording
in Boeing Alert Service Bulletin 757–
27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29,
2012. AAL explained that Boeing Alert
Service Bulletin 757–27A0153, dated
May 9, 2012, as revised by Boeing Alert
Service Bulletin 757–27A0153, Revision
1, dated October 29, 2012, refers to bolt
part number (P/N) BACB30NM5DK47 as
changed to P/N BACB30UU5K48D as
the rudder pedal pushrod bolt, while
the NPRM refers to this part number as
the rudder pedal pushrod connecting
bolt. AAL expressed that matching the
terminology in Boeing Alert Service
Bulletin 757–27A0153, dated May 9,
2012, as revised by Boeing Alert Service
Bulletin 757–27A0153, Revision 1,
dated October 29, 2012, would
eliminate any possible confusion.
We disagree with the request to match
the terminology in this final rule with
the terminology found in Boeing Alert
Service Bulletin 757–27A0153, dated
May 9, 2012, as revised by Boeing Alert
Service Bulletin 757–27A0153, Revision
1, dated October 29, 2012. The word
‘‘connecting’’ was added in the NPRM
(78 FR 27315, May 10, 2013) to further
clarify that this bolt secures the rudder
pedal arm to the rudder pushrod. We
have not changed this final rule in this
regard.
Request To Use Specific Instructions
AAL requested that we revise the
NPRM (78 FR 27315, May 10, 2013) to
require only those instructions that
correct the unsafe condition. AAL
explained that paragraphs (g) and (h) of
the NPRM are more restrictive than
necessary to ensure safety of flight, and
that the Accomplishment Instructions of
Boeing Alert Service Bulletin 757–
27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29,
2012, should not be mandated in their
entirety.
AAL requested the following
revisions to certain paragraphs of the
NPRM (78 FR 27315, May 10, 2013):
• Since paragraph (g) of the NPRM
(78 FR 27315, May 10, 2013) specified
a detailed inspection of the rudder
pedal assembly bolt holes, the only
procedure that should be mandated by
this paragraph is FIGURE 1 of the
Accomplishment Instructions of Boeing
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Alert Service Bulletin 757–27A0153,
dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757–27A0153,
Revision 1, dated October 29, 2012.
• Since paragraph (h)(1) of the NPRM
(78 FR 27315, May 10, 2013) specified
replacement of a new bolt, washer, nut,
and cotter pin, the only procedure that
should be mandated by this paragraph
is FIGURE 2 of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 757–27A0153, dated May 9,
2012, as revised by Boeing Alert Service
Bulletin 757–27A0153, Revision 1,
dated October 29, 2012.
• Paragraph (h)(2)(i) of the NPRM (78
FR 27315, May 10, 2013) should be
revised as follows: ‘‘Install a new rudder
pedal assembly in accordance with
‘Condition 2’ of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 757–27A0153, dated May 9,
2012, as revised by Boeing Alert Service
Bulletin 757–27A0153, Revision 1,
dated October 29, 2012; or install a
bushing in the worn hole in accordance
with FIGURE 3 of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 757–27A0153, dated May 9,
2012, as revised by Boeing Alert Service
Bulletin 757–27A0153, Revision 1,
dated October 29, 2012.’’
• Paragraph (h)(2)(ii) of the NPRM (78
FR 27315, May 10, 2013) specified
installation of a new bolt, washer, nut,
and cotter pin in accordance with the
Accomplishment Instructions of Boeing
Alert Service Bulletin 757–27A0153,
dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757–27A0153,
Revision 1, dated October 29, 2012.
However, Boeing Alert Service Bulletin
757–27A0153, dated May 9, 2012, as
revised by Boeing Alert Service Bulletin
757–27A0153, Revision 1, dated
October 29, 2012, does not provide
explicit instructions to replace the bolt,
washer, nut, and cotter pin in the event
that the diameter of only one hole is
greater than 0.3140 inch. There is only
a note in the procedure to make sure to
discard the existing hardware, and to
install new hardware as provided in
Boeing Kit 0l2N8932–21.
AAL has determined that the
instructions provided in FIGURE 2 of
the Accomplishment Instructions of
Boeing Alert Service Bulletin 757–
27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29,
2012, contain the proper instructions
and part numbers to replace the bolt,
washer, nut, and cotter pin to correct
the unsafe condition. Therefore, the
only procedure that should be mandated
by this paragraph is FIGURE 2 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 757–27A0153,
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14989
dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757–27A0153,
Revision 1, dated October 29, 2012.
• Paragraph (h)(3)(i) of the NPRM (78
FR 27315, May 10, 2013) should be
revised as follows: ‘‘Install a new rudder
pedal assembly in accordance with
‘Condition 2’ of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 757–27A0153, dated May 9,
2012, as revised by Boeing Alert Service
Bulletin 757–27A0153, Revision 1,
dated October 29, 2012, or install two
bushings in the two worn holes in
accordance with FIGURE 4 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin757–27A0153,
dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757–27A0153,
Revision 1, dated October 29, 2012.’’
• Paragraph (h)(3)(ii) of the NPRM (78
FR 27315, May 10, 2013) requires
installation of a new bolt, washer, nut,
and cotter pin in accordance with the
Accomplishment Instructions of Boeing
Alert Service Bulletin 757–27A0153,
dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757–27A0153,
Revision 1, dated October 29, 2012.
However, Boeing Alert Service Bulletin
757–27A0153, dated May 9, 2012, as
revised by Boeing Alert Service Bulletin
757–27A0153, Revision 1, dated
October 29, 2012, does not provide
explicit instructions to replace the bolt,
washer, nut, and cotter pin in the event
that the diameters of both holes are
greater than 0.3140 inch. Again, there is
only a note in the procedure to make
sure to discard the existing hardware,
and to install new hardware as provided
in Boeing Kit 012N8932–21.
AAL has determined that the
instructions provided in FIGURE 2 of
the Accomplishment Instructions of
Boeing Alert Service Bulletin 757–
27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29,
2012, contain the proper instructions
and part numbers to replace the bolt,
washer, nut, and cotter pin to correct
the unsafe condition. Therefore, the
only procedure that should be mandated
by this paragraph is FIGURE 2 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 757–27A0153,
dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757–27A0153,
Revision 1, dated October 29, 2012.
We agree with the concept of
minimizing AD requirements when
appropriate. However, we do not agree
with AAL’s request. The FAA worked in
conjunction with industry, under the
Airworthiness Directives
Implementation Aviation Rulemaking
Committee (ARC), to enhance the AD
system. One enhancement is a new
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process for annotating which steps in
the service information are ‘‘required for
compliance’’ (RC) with an AD.
Differentiating these steps from other
tasks in the service information is
expected to improve an owner’s/
operator’s understanding of AD
requirements and help provide
consistent judgment in AD compliance.
In response to the AD Implementation
ARC, the FAA released AC 20–176,
dated December 19, 2011 (https://
rgl.avs.faa.gov/Regulatory_and_
Guidance_Library/
rgAdvisoryCircular.nsf/0/
a78cc91a47b192278625796b0075f419/
$FILE/AC%2020-176.pdf); and Order
8110.117, dated September 12, 2012
(https://rgl.avs.faa.gov/Regulatory_and_
Guidance_Library/rgOrders.nsf/0/
984bb9eb07cdd86986257a7f0070744c/
$FILE/Order%208110.117.pdf), which
include the concept of RC. The FAA has
begun implementing this concept in
ADs when we receive service
information containing RC steps. While
some design approval holders have
implemented the RC concept, the
implementation is voluntary. The FAA
does not intend to develop or revise AD
requirements to incorporate the RC
concept if it is not included in the
service information.
Contrary to AAL’s statement that ADs
should mandate only those service
bulletin provisions that are ‘‘necessary
to ensure safety of flight,’’ ADs generally
contain requirements that are
reasonably related to addressing the
unsafe condition, as determined by the
FAA and the design approval holder
that developed the service bulletin.
Typically, operators’ maintenance
programs were not developed in
recognition of the unsafe condition that
is being addressed by an AD. Whenever
we issue an AD, those programs had
failed to prevent the unsafe condition in
the first place. Therefore, many
provisions of ADs address aspects of
accomplishing the required
maintenance that are necessary to
prevent operators from inadvertently
aggravating the unsafe condition or
introducing new unsafe conditions.
For many years, the Air Transport
Association (now Airlines for America,
A4A) has sponsored the ‘‘Lead Airline’’
program through which individual
airlines are provided an opportunity to
prototype manufacturers’ draft service
instructions before they are finalized.
One objective of this activity is to
minimize the procedures included in
the instructions that are considered
unnecessary. Therefore, when the FAA
receives a manufacturer’s service
bulletin, we recognize that the
procedures specified have been
determined to be necessary by both the
manufacturer and affected operators. As
in this case, the instructions provided in
service bulletins referenced in ADs are
reasonably related to addressing the
unsafe condition.
As always, if AAL or any other
operator prefers to address the unsafe
condition by means other than those
specified in the referenced service
information, they may request approval
for an alternative method of compliance
and, if approved, may use it instead of
the procedures specified in the service
information.
Therefore, no changes have been
made to this final rule in this regard.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
27315, May 10, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 27315,
May 10, 2013).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 685
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Parts
cost
Labor cost
Inspect/replace bolts (Condition 1 in the Accomplishment Instructions of Boeing Alert Service
Bulletin 757–27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29, 2012).
We estimate the following costs to do
any necessary repairs/replacements that
5 work-hours × $85 per
hour = $425 per inspection cycle.
$217
Cost per product
$642 per inspection
cycle.
would be required based on the results
of the inspection. We have no way of
Cost on U.S. operators
$439,770 per inspection
cycle
determining the number of aircraft that
might need these repairs/replacements:
ON-CONDITION COSTS
sroberts on DSK5SPTVN1PROD with RULES
Action
Labor cost
Replace rudder pedal assembly (Condition 2 in the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012,
as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1,
dated October 29, 2012).
Repair rudder pedal assembly (Condition 3 in the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012,
as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1,
dated October 29, 2012).
VerDate Mar<15>2010
17:18 Mar 17, 2014
Jkt 232001
PO 00000
Frm 00014
Fmt 4700
Parts cost
Cost per
product
2 work-hours × $85 per hour = $170
Unknown ....
$170
3 work-hours × $85 per hour = $255
Unknown ....
$255
Sfmt 4700
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18MRR1
Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations
14991
ON-CONDITION COSTS—Continued
Action
Labor cost
Repair rudder pedal assembly (Condition 4 in the Accomplishment Instructions of Boeing Alert Service Bulletin 757–27A0153, dated May 9, 2012,
as revised by Boeing Alert Service Bulletin 757–27A0153, Revision 1,
dated October 29, 2012).
4 work-hours × $85 per hour = $340
The on-condition costs in the table
above are per rudder pedal assembly.
Depending on the diameter of the holes
found during the inspection, it may be
necessary to replace or repair the rudder
pedal assemblies. The parts cost to
replace or repair the rudder pedal
assemblies are not included in the
estimate; it is considered ‘‘Parts &
Materials Supplied by the Operator,’’
which is referenced in Boeing Alert
Service Bulletin 757–27A0153, dated
May 9, 2012, as revised by Boeing Alert
Service Bulletin 757–27A0153, Revision
1, dated October 29, 2012.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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.
Authority for This Rulemaking
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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.
sroberts on DSK5SPTVN1PROD with RULES
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
VerDate Mar<15>2010
17:18 Mar 17, 2014
Jkt 232001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2014–05–20 The Boeing Company:
Amendment 39–17793; Docket No.
FAA–2013–0369; Directorate Identifier
2012–NM–128–AD.
(a) Effective Date
This AD is effective April 22, 2014.
(b) Affected ADs
Certain requirements of this AD terminate
the requirements of AD 2001–22–13,
Amendment 39–12492 (66 FR 55075,
November 1, 2001), for Model 757 airplanes.
(c) Applicability
This AD applies to all The Boeing
Company Model 757–200, –200PF, –200CB,
and –300 series airplanes, certificated in any
category.
PO 00000
Frm 00015
Fmt 4700
Parts cost
Sfmt 4700
Cost per
product
Unknown ....
$340
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Unsafe Condition
This AD was prompted by reports of
fractured rudder pedal pushrod connecting
bolts in the rudder pedal assembly. We are
issuing this AD to prevent fracture of the
rudder pedal pushrod connecting bolts
during pedal use, which could result in large
involuntary inputs to the rudder and nosewheel steering and an asymmetric
application of braking, if pedal brakes are
applied, leading to a runway excursion.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection
Within 60 months after the effective date
of this AD, do a detailed inspection of the
rudder pedal assembly bolt holes to
determine the diameter in each of the captain
and the first officer rudder pedal assemblies,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29, 2012.
Repeat this inspection thereafter at intervals
not to exceed 15,000 flight cycles.
(h) Installation
Do the applicable actions specified in
paragraph (h)(1), (h)(2), or (h)(3) of this AD
for each of the captain and first officer rudder
pedal assemblies, based on the results of any
inspection required by paragraph (g) of this
AD. Accomplishment of paragraph (h)(1),
(h)(2), or (h)(3) of this AD terminates the
requirements of AD 2001–22–13,
Amendment 39–12492 (66 FR 55075,
November 1, 2001), for that Model 757
airplane only.
(1) If the diameters of both holes are within
0.3120 and 0.3140 inch on the assembly,
before further flight, install a new rudder
pedal pushrod connecting bolt, washer, nut,
and cotter pin, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 757–27A0153, dated May 9,
2012, as revised by Boeing Alert Service
Bulletin 757–27A0153, Revision 1, dated
October 29, 2012.
(2) If the diameter of only one hole is
greater than 0.3140 inch on the assembly,
before further flight, do the actions specified
in paragraphs (h)(2)(i) and (h)(2)(ii) of this
AD.
(i) Install a new rudder pedal assembly, or
install a bushing in the worn hole, in
accordance with the Accomplishment
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14992
Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations
Instructions of Boeing Alert Service Bulletin
757–27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29, 2012.
(ii) Install a new rudder pedal pushrod
connecting bolt, washer, nut, and cotter pin,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29, 2012.
(3) If the diameters of both holes are greater
than 0.3140 inch on the assembly, before
further flight, do the actions specified in
paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.
(i) Install a new rudder pedal assembly, or
install two bushings in the two worn holes,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29, 2012.
(ii) Install a new rudder pedal pushrod
connecting bolt, washer, nut, and cotter pin,
in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29, 2012.
(i) Parts Installation Prohibition
As of the effective date of this AD, no
person may install, in a rudder pedal
assembly of any Boeing Model 757 airplane,
a bolt having part number (P/N)
BACB30NM5DK47.
sroberts on DSK5SPTVN1PROD with RULES
(j) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (g) and (h) of
this AD, if operators installed washers having
P/N NAS1149D0516J, NAS1149D0532J, and
NAS1149D0563J, and if those actions were
performed before the effective date of this AD
using Boeing Alert Service Bulletin 757–
27A0153, dated May 9, 2012, as unmodified
by Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29, 2012.
(k) Alternative Methods of Compliance
(AMOCs)
(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
paragraph (l)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) 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.
(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
VerDate Mar<15>2010
17:18 Mar 17, 2014
Jkt 232001
the certification basis of the airplane, and the
approval must specifically refer to this AD.
DEPARTMENT OF TRANSPORTATION
(l) Related Information
Federal Aviation Administration
(1) For more information about this AD,
contact Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, ANM–130S,
Seattle Aircraft Certification Office, FAA,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6418; fax: 425–917–
6590; email: marie.hogestad@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference in
this AD may be obtained at the address
specified in paragraphs (m)(3) and (m)(4) of
this AD.
14 CFR Part 39
(m) 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) Boeing Alert Service Bulletin 757–
27A0153, dated May 9, 2012.
(ii) Boeing Alert Service Bulletin 757–
27A0153, Revision 1, dated October 29, 2012.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P. O. Box 3707, MC
2H–65, Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at FAA, 1601 Lind Avenue SW., Renton, WA
98057–3356. 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 February
19, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–04843 Filed 3–17–14; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
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Fmt 4700
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[Docket No. FAA–2013–0327; Directorate
Identifier 2011–NM–161–AD; Amendment
39–17794; AD 2014–05–21]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2008–11–
04 for all The Boeing Company Model
737–100, –200, –200C, –300, –400, and
–500 series airplanes. AD 2008–11–04
required repetitive inspections for
cracking in and around the upper and
lower hinge cutouts of the forward entry
and forward galley service doorways,
and corrective actions if necessary. This
new AD reduces the inspection
threshold for cracking in and around the
galley service doorway hinge cutouts,
adds inspections of certain repaired
structure at the forward entry and galley
service doorway upper and lower hinge
cutouts, expands the inspection area at
the forward entry and galley service
doorway upper and lower hinge cutouts,
and removes certain airplanes from the
applicability. This AD was prompted by
multiple reports of cracks in the skin
and/or bear strap at the forward galley
service doorway hinge cutouts, and
multiple reports of cracking under the
repairs installed at the hinge cutouts.
We are issuing this AD to detect and
correct such cracking, which could
result in rapid decompression of the
airplane.
SUMMARY:
This AD is effective April 22,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 22, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of June 25, 2008 (73 FR
29421, May 21, 2008).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P. O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
phone: 206–544–5000, extension 1; fax:
206–766–5680; Internet: https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
DATES:
E:\FR\FM\18MRR1.SGM
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]]>Agencies
[Federal Register Volume 79, Number 52 (Tuesday, March 18, 2014)]
[Rules and Regulations]
[Pages 14987-14992]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04843]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0369; Directorate Identifier 2012-NM-128-AD;
Amendment 39-17793; AD 2014-05-20]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 757 airplanes. This AD was prompted by reports of
fractured rudder pedal pushrod connecting bolts in a rudder pedal
assembly. This AD requires repetitive replacements of the rudder pedal
pushrod connecting bolts and repetitive inspections of the rudder pedal
assembly bolt holes in each of the captain and the first officer rudder
pedal assemblies, and if necessary, repair or replacement of worn
rudder pedal assemblies. We are issuing this AD to prevent fracture of
the rudder pedal pushrod connecting bolts during pedal use, which could
result in large involuntary inputs to the rudder and nose-wheel
steering and an asymmetric application of braking, if pedal brakes are
applied, leading to a runway excursion.
DATES: This AD is effective April 22, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of April 22,
2014.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, Washington 98057-3356. 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 by searching for and locating Docket No. FAA-2013-
0369; 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 address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, Seattle Aircraft Certification
Office, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6418; fax: 425-917-6590; email: marie.hogestad@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all The Boeing Company
Model 757 airplanes. The NPRM published in the Federal Register on May
10, 2013 (78 FR 27315). The NPRM was prompted by reports of fractured
rudder pedal pushrod connecting bolts in a rudder pedal assembly. The
NPRM proposed to require repetitive
[[Page 14988]]
replacements of the rudder pedal pushrod connecting bolts and
repetitive inspections of the rudder pedal assembly bolt holes in each
of the captain and the first officer rudder pedal assemblies, and if
necessary, repair or replacement of worn rudder pedal assemblies. We
are issuing this AD to prevent fracture of the rudder pedal pushrod
connecting bolts during pedal use, which could result in large
involuntary inputs to the rudder and nose-wheel steering and an
asymmetric application of braking, if pedal brakes are applied, leading
to a runway excursion.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(78 FR 27315, May 10, 2013) and the FAA's response to each comment.
Request To Reduce the Compliance Time
Air Line Pilots Association International (the commenter) stated
that it agrees with the intent of the NPRM (78 FR 27315, May 10, 2013),
but requested that we reduce the compliance time from 60 months to 24
months. The commenter provided no justification for this request.
We disagree with the request to revise the compliance time in this
final rule. In developing the compliance time for this final rule, we
considered not only the safety implications of the identified unsafe
condition, but also the average utilization rate of the affected fleet,
the practical aspects of an orderly modification of the fleet, the
availability of required parts, and the time necessary for the
rulemaking process. We find that the compliance time, as proposed,
adequately represents an appropriate interval of time in which the
required actions can be performed in a timely manner within the
affected fleet, while still maintaining an adequate level of safety. We
have not changed this final rule in this regard.
Request To Clarify the Unsafe Condition
Boeing requested that we revise the unsafe condition in the NPRM
(78 FR 27315, May 10, 2013), and suggested language to clarify the
expectation of asymmetric braking, in the event of fracture of the
subject bolt. Boeing added that symmetric braking inputs prior to
fracture can become asymmetric following bolt fracture due to loss of
brake inputs on the affected side.
We agree with the request to revise the unsafe condition for the
reasons provided by Boeing. We have revised this final rule to reflect
the revised language.
Request To Use One Service Bulletin Revision
Aviation Technical Services, Inc. (the commenter) requested that we
revise the NPRM (78 FR 27315, May 10, 2013) to mandate only one version
of the service information. The commenter also requested that we
require that Boeing combine both versions of the service bulletin
specified in the NPRM, into one final revision. The commenter reasoned
that having two versions of the service bulletin will require operators
and maintenance providers to integrate the two service bulletins in
order to comply with the NPRM. The commenter expressed that this burden
should be on the original equipment manufacturer (OEM) and the FAA.
The commenter also requested that to further determine the adequacy
of Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, as
revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated
October 29, 2012, the FAA should use its own guidance, as provided by
FAA Advisory Circular (AC) 20-176, dated December 19, 2011 (https://
rgl.avs.faa.gov/Regulatory--and--Guidance--Library/
rgAdvisoryCircular.nsf/0/a78cc91a47b192278625796b0075f419/$FILE/
AC%2020-176.pdf).
We disagree with the request to provide a single service bulletin
version for the required method of compliance. Boeing Alert Service
Bulletin 757-27A0153, Revision 1, dated October 29, 2012, includes only
minor corrections to washer part numbers in top kit 012N8932-21 and an
additional instruction for getting better access, if necessary, for the
detailed inspections required by this final rule. It is not necessary
that Boeing combine both revisions of the referenced service bulletin
into one final revision.
Also, the design approval holder (DAH) followed the guidance in FAA
AC 20-176, dated December 19, 2011 (https://rgl.avs.faa.gov/Regulatory--
and--Guidance--Library/rgAdvisoryCircular.nsf/0/
a78cc91a47b192278625796b0075f419/$FILE/AC%2020-176.pdf). We approved
Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, as
revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated
October 29, 2012, using the guidance in FAA Order 8110.117, dated
September 12, 2012 (https://rgl.avs.faa.gov/Regulatory--and--Guidance--
Library/rgOrders.nsf/0/984bb9eb07cdd86986257a7f0070744c/$FILE/
Order%208110.117.pdf). (Refer to Section 2-11, ``Streamlining
Development and Revision of SBs,'' paragraph (c)(5), ``Partial Revision
Process--A process in which only changed information in a service
bulletin is sent to affected customers,'' of FAA AC 20-176, dated
December 19, 2011.) We have not changed this final rule in this regard.
Request for Additional Guidance
Aviation Technical Services, Inc. (the commenter) requested that we
revise the NPRM (78 FR 27315, May 10, 2013) to provide sufficient
instruction to determine the installation finish associated with the
replacement bushing for the rudder pedal pushrod. The commenter
reasoned that the instructions provided by Boeing Alert Service
Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing Alert
Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012, refer
to Boeing Standard Overhaul Practices Manual (SOPM) 20-50-03 for the
shrink fit procedure to install repair bushings, and that the SOPM
procedure contain instructions such as: ``Apply the specified
installation finish. . . .'' and ``Refer to the overhaul instructions
for applicable operations. . . .'' The commenter asserted that neither
Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, as
revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated
October 29, 2012, nor the SOPM provide sufficient instruction to
determine the installation finish associated with the replacement
bushing for the rudder pedal pushrod.
We disagree to revise this final rule. Step 4 of Figures 3 and 4 of
the Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin
757-27A0153, Revision 1, dated October 29, 2012, already provides
procedures for installing bushing 001N0004-1 with BMS 5-95 sealant, as
specified in ``the shrink fit'' procedure referred to in Standard
Overhaul Practices Manual (SOPM) 20-50-03 (bushing 001N0004-1 is
already finished). SOPM 20-50-03 Bearing and Bushing Replacement,
Paragraph 7.B, ``Shrink Fit (Temperature Differential) Procedure,''
specifies, among other things, to apply the specified installation
finish ``as specified in Paragraph 6B,'' which, in turn, specifies
``Installation with sealant.'' The finish is, in this case, the sealant
that is used during the installation (BMS 5-95). Therefore, Boeing
Alert Service Bulletin 757-27A0153, dated May 9, 2012, as revised by
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October
29,
[[Page 14989]]
2012, in combination with SOPM 20-50-03, provide sufficient
instructions to install the bushing. We have not changed the AD in this
regard.
Request To Match Terminology
American Airlines (AAL) requested that we revise the NPRM (78 FR
27315, May 10, 2013) to match certain wording in Boeing Alert Service
Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing Alert
Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012. AAL
explained that Boeing Alert Service Bulletin 757-27A0153, dated May 9,
2012, as revised by Boeing Alert Service Bulletin 757-27A0153, Revision
1, dated October 29, 2012, refers to bolt part number (P/N)
BACB30NM5DK47 as changed to P/N BACB30UU5K48D as the rudder pedal
pushrod bolt, while the NPRM refers to this part number as the rudder
pedal pushrod connecting bolt. AAL expressed that matching the
terminology in Boeing Alert Service Bulletin 757-27A0153, dated May 9,
2012, as revised by Boeing Alert Service Bulletin 757-27A0153, Revision
1, dated October 29, 2012, would eliminate any possible confusion.
We disagree with the request to match the terminology in this final
rule with the terminology found in Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin
757-27A0153, Revision 1, dated October 29, 2012. The word
``connecting'' was added in the NPRM (78 FR 27315, May 10, 2013) to
further clarify that this bolt secures the rudder pedal arm to the
rudder pushrod. We have not changed this final rule in this regard.
Request To Use Specific Instructions
AAL requested that we revise the NPRM (78 FR 27315, May 10, 2013)
to require only those instructions that correct the unsafe condition.
AAL explained that paragraphs (g) and (h) of the NPRM are more
restrictive than necessary to ensure safety of flight, and that the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin
757-27A0153, Revision 1, dated October 29, 2012, should not be mandated
in their entirety.
AAL requested the following revisions to certain paragraphs of the
NPRM (78 FR 27315, May 10, 2013):
Since paragraph (g) of the NPRM (78 FR 27315, May 10,
2013) specified a detailed inspection of the rudder pedal assembly bolt
holes, the only procedure that should be mandated by this paragraph is
FIGURE 1 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing Alert
Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012.
Since paragraph (h)(1) of the NPRM (78 FR 27315, May 10,
2013) specified replacement of a new bolt, washer, nut, and cotter pin,
the only procedure that should be mandated by this paragraph is FIGURE
2 of the Accomplishment Instructions of Boeing Alert Service Bulletin
757-27A0153, dated May 9, 2012, as revised by Boeing Alert Service
Bulletin 757-27A0153, Revision 1, dated October 29, 2012.
Paragraph (h)(2)(i) of the NPRM (78 FR 27315, May 10,
2013) should be revised as follows: ``Install a new rudder pedal
assembly in accordance with `Condition 2' of the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 9,
2012, as revised by Boeing Alert Service Bulletin 757-27A0153, Revision
1, dated October 29, 2012; or install a bushing in the worn hole in
accordance with FIGURE 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 757-27A0153, dated May 9, 2012, as revised by
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October
29, 2012.''
Paragraph (h)(2)(ii) of the NPRM (78 FR 27315, May 10,
2013) specified installation of a new bolt, washer, nut, and cotter pin
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012.
However, Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012,
as revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1,
dated October 29, 2012, does not provide explicit instructions to
replace the bolt, washer, nut, and cotter pin in the event that the
diameter of only one hole is greater than 0.3140 inch. There is only a
note in the procedure to make sure to discard the existing hardware,
and to install new hardware as provided in Boeing Kit 0l2N8932-21.
AAL has determined that the instructions provided in FIGURE 2 of
the Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin
757-27A0153, Revision 1, dated October 29, 2012, contain the proper
instructions and part numbers to replace the bolt, washer, nut, and
cotter pin to correct the unsafe condition. Therefore, the only
procedure that should be mandated by this paragraph is FIGURE 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin
757-27A0153, Revision 1, dated October 29, 2012.
Paragraph (h)(3)(i) of the NPRM (78 FR 27315, May 10,
2013) should be revised as follows: ``Install a new rudder pedal
assembly in accordance with `Condition 2' of the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 9,
2012, as revised by Boeing Alert Service Bulletin 757-27A0153, Revision
1, dated October 29, 2012, or install two bushings in the two worn
holes in accordance with FIGURE 4 of the Accomplishment Instructions of
Boeing Alert Service Bulletin757-27A0153, dated May 9, 2012, as revised
by Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October
29, 2012.''
Paragraph (h)(3)(ii) of the NPRM (78 FR 27315, May 10,
2013) requires installation of a new bolt, washer, nut, and cotter pin
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing
Alert Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012.
However, Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012,
as revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1,
dated October 29, 2012, does not provide explicit instructions to
replace the bolt, washer, nut, and cotter pin in the event that the
diameters of both holes are greater than 0.3140 inch. Again, there is
only a note in the procedure to make sure to discard the existing
hardware, and to install new hardware as provided in Boeing Kit
012N8932-21.
AAL has determined that the instructions provided in FIGURE 2 of
the Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin
757-27A0153, Revision 1, dated October 29, 2012, contain the proper
instructions and part numbers to replace the bolt, washer, nut, and
cotter pin to correct the unsafe condition. Therefore, the only
procedure that should be mandated by this paragraph is FIGURE 2 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin
757-27A0153, Revision 1, dated October 29, 2012.
We agree with the concept of minimizing AD requirements when
appropriate. However, we do not agree with AAL's request. The FAA
worked in conjunction with industry, under the Airworthiness Directives
Implementation Aviation Rulemaking Committee (ARC), to enhance the AD
system. One enhancement is a new
[[Page 14990]]
process for annotating which steps in the service information are
``required for compliance'' (RC) with an AD. Differentiating these
steps from other tasks in the service information is expected to
improve an owner's/operator's understanding of AD requirements and help
provide consistent judgment in AD compliance.
In response to the AD Implementation ARC, the FAA released AC 20-
176, dated December 19, 2011 (https://rgl.avs.faa.gov/Regulatory--and--
Guidance--Library/rgAdvisoryCircular.nsf/0/
a78cc91a47b192278625796b0075f419/$FILE/AC%2020-176.pdf); and Order
8110.117, dated September 12, 2012 (https://rgl.avs.faa.gov/Regulatory--
and--Guidance--Library/rgOrders.nsf/0/984bb9eb07cdd86986257a7f0070744c/
$FILE/Order%208110.117.pdf), which include the concept of RC. The FAA
has begun implementing this concept in ADs when we receive service
information containing RC steps. While some design approval holders
have implemented the RC concept, the implementation is voluntary. The
FAA does not intend to develop or revise AD requirements to incorporate
the RC concept if it is not included in the service information.
Contrary to AAL's statement that ADs should mandate only those
service bulletin provisions that are ``necessary to ensure safety of
flight,'' ADs generally contain requirements that are reasonably
related to addressing the unsafe condition, as determined by the FAA
and the design approval holder that developed the service bulletin.
Typically, operators' maintenance programs were not developed in
recognition of the unsafe condition that is being addressed by an AD.
Whenever we issue an AD, those programs had failed to prevent the
unsafe condition in the first place. Therefore, many provisions of ADs
address aspects of accomplishing the required maintenance that are
necessary to prevent operators from inadvertently aggravating the
unsafe condition or introducing new unsafe conditions.
For many years, the Air Transport Association (now Airlines for
America, A4A) has sponsored the ``Lead Airline'' program through which
individual airlines are provided an opportunity to prototype
manufacturers' draft service instructions before they are finalized.
One objective of this activity is to minimize the procedures included
in the instructions that are considered unnecessary. Therefore, when
the FAA receives a manufacturer's service bulletin, we recognize that
the procedures specified have been determined to be necessary by both
the manufacturer and affected operators. As in this case, the
instructions provided in service bulletins referenced in ADs are
reasonably related to addressing the unsafe condition.
As always, if AAL or any other operator prefers to address the
unsafe condition by means other than those specified in the referenced
service information, they may request approval for an alternative
method of compliance and, if approved, may use it instead of the
procedures specified in the service information.
Therefore, no changes have been made to this final rule in this
regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 27315, May 10, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 27315, May 10, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 685 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspect/replace bolts (Condition 1 5 work-hours x $85 $217 $642 per inspection $439,770 per
in the Accomplishment per hour = $425 per cycle. inspection cycle
Instructions of Boeing Alert inspection cycle.
Service Bulletin 757-27A0153,
dated May 9, 2012, as revised by
Boeing Alert Service Bulletin 757-
27A0153, Revision 1, dated
October 29, 2012).
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the
inspection. We have no way of determining the number of aircraft that
might need these repairs/replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace rudder pedal assembly (Condition 2 in 2 work-hours x $85 per hour Unknown............... $170
the Accomplishment Instructions of Boeing = $170.
Alert Service Bulletin 757-27A0153, dated May
9, 2012, as revised by Boeing Alert Service
Bulletin 757-27A0153, Revision 1, dated
October 29, 2012).
Repair rudder pedal assembly (Condition 3 in 3 work-hours x $85 per hour Unknown............... $255
the Accomplishment Instructions of Boeing = $255.
Alert Service Bulletin 757-27A0153, dated May
9, 2012, as revised by Boeing Alert Service
Bulletin 757-27A0153, Revision 1, dated
October 29, 2012).
[[Page 14991]]
Repair rudder pedal assembly (Condition 4 in 4 work-hours x $85 per hour Unknown............... $340
the Accomplishment Instructions of Boeing = $340.
Alert Service Bulletin 757-27A0153, dated May
9, 2012, as revised by Boeing Alert Service
Bulletin 757-27A0153, Revision 1, dated
October 29, 2012).
----------------------------------------------------------------------------------------------------------------
The on-condition costs in the table above are per rudder pedal
assembly. Depending on the diameter of the holes found during the
inspection, it may be necessary to replace or repair the rudder pedal
assemblies. The parts cost to replace or repair the rudder pedal
assemblies are not included in the estimate; it is considered ``Parts &
Materials Supplied by the Operator,'' which is referenced in Boeing
Alert Service Bulletin 757-27A0153, dated May 9, 2012, as revised by
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October
29, 2012.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2014-05-20 The Boeing Company: Amendment 39-17793; Docket No. FAA-
2013-0369; Directorate Identifier 2012-NM-128-AD.
(a) Effective Date
This AD is effective April 22, 2014.
(b) Affected ADs
Certain requirements of this AD terminate the requirements of AD
2001-22-13, Amendment 39-12492 (66 FR 55075, November 1, 2001), for
Model 757 airplanes.
(c) Applicability
This AD applies to all The Boeing Company Model 757-200, -200PF,
-200CB, and -300 series airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Unsafe Condition
This AD was prompted by reports of fractured rudder pedal
pushrod connecting bolts in the rudder pedal assembly. We are
issuing this AD to prevent fracture of the rudder pedal pushrod
connecting bolts during pedal use, which could result in large
involuntary inputs to the rudder and nose-wheel steering and an
asymmetric application of braking, if pedal brakes are applied,
leading to a runway excursion.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
Within 60 months after the effective date of this AD, do a
detailed inspection of the rudder pedal assembly bolt holes to
determine the diameter in each of the captain and the first officer
rudder pedal assemblies, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153,
Revision 1, dated October 29, 2012. Repeat this inspection
thereafter at intervals not to exceed 15,000 flight cycles.
(h) Installation
Do the applicable actions specified in paragraph (h)(1), (h)(2),
or (h)(3) of this AD for each of the captain and first officer
rudder pedal assemblies, based on the results of any inspection
required by paragraph (g) of this AD. Accomplishment of paragraph
(h)(1), (h)(2), or (h)(3) of this AD terminates the requirements of
AD 2001-22-13, Amendment 39-12492 (66 FR 55075, November 1, 2001),
for that Model 757 airplane only.
(1) If the diameters of both holes are within 0.3120 and 0.3140
inch on the assembly, before further flight, install a new rudder
pedal pushrod connecting bolt, washer, nut, and cotter pin, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 757-27A0153, dated May 9, 2012, as revised by
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October
29, 2012.
(2) If the diameter of only one hole is greater than 0.3140 inch
on the assembly, before further flight, do the actions specified in
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Install a new rudder pedal assembly, or install a bushing in
the worn hole, in accordance with the Accomplishment
[[Page 14992]]
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153,
Revision 1, dated October 29, 2012.
(ii) Install a new rudder pedal pushrod connecting bolt, washer,
nut, and cotter pin, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153,
Revision 1, dated October 29, 2012.
(3) If the diameters of both holes are greater than 0.3140 inch
on the assembly, before further flight, do the actions specified in
paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.
(i) Install a new rudder pedal assembly, or install two bushings
in the two worn holes, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153,
Revision 1, dated October 29, 2012.
(ii) Install a new rudder pedal pushrod connecting bolt, washer,
nut, and cotter pin, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153,
Revision 1, dated October 29, 2012.
(i) Parts Installation Prohibition
As of the effective date of this AD, no person may install, in a
rudder pedal assembly of any Boeing Model 757 airplane, a bolt
having part number (P/N) BACB30NM5DK47.
(j) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g) and (h) of this AD, if operators installed washers
having P/N NAS1149D0516J, NAS1149D0532J, and NAS1149D0563J, and if
those actions were performed before the effective date of this AD
using Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012,
as unmodified by Boeing Alert Service Bulletin 757-27A0153, Revision
1, dated October 29, 2012.
(k) Alternative Methods of Compliance (AMOCs)
(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 paragraph (l)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) 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.
(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.
(l) Related Information
(1) For more information about this AD, contact Marie Hogestad,
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, Seattle
Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, WA
98057-3356; phone: 425-917-6418; fax: 425-917-6590; email:
marie.hogestad@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference in this AD may be obtained at the address
specified in paragraphs (m)(3) and (m)(4) of this AD.
(m) 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) Boeing Alert Service Bulletin 757-27A0153, dated May 9,
2012.
(ii) Boeing Alert Service Bulletin 757-27A0153, Revision 1,
dated October 29, 2012.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet
https://www.myboeingfleet.com.
(4) You may view this service information at FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356. 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/ibr-locations.html.
Issued in Renton, Washington, on February 19, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-04843 Filed 3-17-14; 8:45 am]
BILLING CODE 4910-13-P
