[Federal Register Volume 78, Number 91 (Friday, May 10, 2013)]
[Proposed Rules]
[Pages 27315-27318]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-11168]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0369; Directorate Identifier 2012-NM-128-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 757 airplanes. This proposed AD was prompted
by reports of fractured rudder pedal pushrod connecting bolts in a
rudder pedal assembly. This proposed AD would require 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 proposing this AD to prevent fracture of the rudder pedal pushrod
connecting bolts during pedal use, which could result in a large
involuntary input to the rudder, nose-wheel steering, and braking
systems, leading to a runway excursion.
DATES: We must receive comments on this proposed AD by June 24, 2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
[[Page 27316]]
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed 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 review copies of the 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 http://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 proposed 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: Marie Hogestad, Aerospace Engineer,
Systems and Equipment Branch, FAA, ANM-130S, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-
3356; phone: 425-917-6418; fax: 425-917-6590; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2013-0369;
Directorate Identifier 2012-NM-128-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We received reports of fractured rudder pedal pushrod connecting
bolts on Boeing Model 757 airplanes. One operator discovered a bolt was
fractured during an inspection, following a report that the captain's
right pedal was loose. Another operator reported a fractured bolt
during the airplane pushback. When the captain applied the brakes, the
right hand rudder pedal collapsed and both pedals fell forward. An
inspection revealed that a rudder pedal pushrod bolt was fractured,
resulting in a full left rudder input. Also, in a separate incident,
during routine maintenance, while the brakes were released, a loud
crack was heard and the right hand rudder pedal went all the way
forward. During investigation, it was determined that the captain's
right hand rudder pedal pushrod bolt had fractured. The rudder pedal
pushrod connecting bolt secures the rudder pedal arm to the rudder
pushrod. The bolt is cantilevered in a single shear arrangement that is
not capable of carrying its design load if there is looseness in the
installation (bolt bending is introduced). The bolts can also rotate,
due to lack of bolt clamp-up, causing additional wear. This condition,
if not corrected, could result in a fracture of the rudder pedal
pushrod connecting bolts during pedal use, which could result in large
involuntary input to the rudder, nose-wheel steering, and braking
systems, leading to a runway excursion.
Related Rulemaking
We issued AD 2001-22-13, Amendment 39-12492 (66 FR 55075, November
1, 2001), for certain Model 737, 747, 757, 767, and 777 series
airplanes. That AD requires replacing the rudder pedal pushrod
fasteners (bolts) for the captain's and first officer's pedal
assemblies with titanium fasteners (bolts).
We have determined that titanium bolts are under-strength on Model
757 airplanes and must be replaced with Inconel bolts. Titanum bolts
do, however, meet the static and fatigue requirements for the other
airplane models affected by AD 2001-22-13, Amendment 39-12492 (66 FR
55075, November 1, 2001).
Relevant Service Information
We reviewed 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. For information on the procedures and
compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2013-0369.
FAA's Determination
We are proposing 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 the same type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously. Replacements of the
rudder pedal pushrod connecting bolts are done after each inspection
specified in paragraph (g) of this AD, regardless of the inspection
results. Some actions would terminate the requirements of AD 2001-22-
13, Amendment 39-12492 (66 FR 55075, November 1, 2001), for Model 757
airplanes.
Costs of Compliance
We estimate that this proposed AD affects 685 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 27317]]
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspect/replace bolts (Condition 5 work-hours x $85 $217 $642 per inspection $439,770 per
1 in the Accomplishment per hour = $425 cycle. inspection cycle.
Instructions of Boeing Alert per inspection
Service Bulletin 757-27A0153, cycle.
dated May 9, 2012, as revised
by Boeing Alert Service
Bulletin 757-27A0153, Revision
1, dated October 29, 2012).
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We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the
proposed inspection. We have no way of determining the number of
aircraft that might need these repairs/replacements:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Replace rudder pedal assembly (Condition 2 in 2 work-hours x $85 per Unknown................ $170
the Accomplishment Instructions of Boeing hour = $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 Unknown................ 255
the Accomplishment Instructions of Boeing hour = $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).
Repair rudder pedal assembly (Condition 4 in 4 work-hours x $85 per Unknown................ 340
the Accomplishment Instructions of Boeing hour = $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).
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The on-condition costs in the table above are per rudder pedal
assembly. Depending on the diamater 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 proposed
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
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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):
The Boeing Company: Docket No. FAA-2013-0369; Directorate Identifier
2012-NM-128-AD.
(a) Comments Due Date
We must receive comments by June 24, 2013.
(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.
[[Page 27318]]
(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
Joint Aircraft System Component (JASC)/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 a large
involuntary input to the rudder, nose-wheel steering, and braking
systems, 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 new rudder
pedal pushrod connect 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 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 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 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
As of the effective date of this AD, no person may install, in a
rudder pedal assembly of any Boeing 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 part number 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, which is not incorporated by reference in this AD, 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 the Related Information
section of this AD. Information may be emailed to: [email protected].
(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, FAA, ANM-130S,
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; phone: 425-917-6418; fax: 425-917-6590;
email: [email protected].
(2) 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 review copies of the 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.
Issued in Renton, Washington, on May 2, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-11168 Filed 5-9-13; 8:45 am]
BILLING CODE 4910-13-P