[Federal Register Volume 78, Number 72 (Monday, April 15, 2013)]
[Proposed Rules]
[Pages 22215-22218]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-08768]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0326; Directorate Identifier 2012-NM-089-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 supersede an existing airworthiness directive
(AD) that applies to certain The Boeing Company Model 757 series
airplanes equipped with Rolls-Royce RB211 engines. The existing AD
currently requires modification of the nacelle strut and wing
structure; for certain airplanes, repetitive detailed inspections of
certain aft bulkhead fasteners for loose or missing fasteners, and
corrective action if necessary. For certain other airplanes, the
existing AD requires a one-time detailed inspection of the middle
gusset of the inboard side load fitting for proper alignment, and
realignment if necessary; a one-time eddy current inspection of certain
fastener holes for cracking, and repair if necessary; a detailed
inspection of certain fasteners for loose or missing fasteners; and
replacement with new fasteners if necessary. Since we issued that AD, a
compliance time error was discovered, which could allow an airplane to
exceed the acceptable compliance time for addressing the unsafe
condition. This proposed AD would specify a maximum compliance time
limit. We are proposing this AD to prevent fatigue cracking in primary
strut structure and consequent reduced structural integrity of the
strut.
DATES: We must receive comments on this proposed AD by May 30, 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.
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 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
review copies of the referenced 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.
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: 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: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0326;
Directorate Identifier 2012-NM-089-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
On May 25, 2004, we issued AD 2004-12-07, Amendment 39-13666 (69 FR
33561, June 16, 2004), for certain Model 757 series airplanes equipped
with Rolls-Royce RB211 engines. (AD 2004-12-07 superseded AD 99-24-07,
Amendment 39-11431 (64 FR 66370, November 26, 1999)). AD 2004-12-07
requires modification of the nacelle strut and wing structure; and for
certain airplanes, repetitive detailed inspections of certain aft
bulkhead fasteners for loose or missing fasteners, and corrective
action if necessary. For certain other airplanes, the existing AD
requires a one-time detailed inspection of the middle gusset of the
inboard side load fitting for proper alignment and realignment if
necessary; a one-time eddy current inspection of certain fastener holes
for cracking, and repair if necessary; a detailed inspection of certain
fasteners for loose or missing fasteners; and replacement with new
fasteners if necessary. That AD resulted from reports indicating that
the actual operational loads applied to the nacelle are higher than the
analytical loads that were used during the initial design. Such an
increase in loading can lead to fatigue cracking in primary strut
[[Page 22216]]
structure prior to an airplane reaching its design service objective.
We issued that AD to prevent fatigue cracking in primary strut
structure and consequent reduced structural integrity of the strut.
Actions Since Existing AD Was Issued
Since we issued AD 2004-12-07, Amendment 39-13666 (69 FR 33561,
June 16, 2004), a compliance time error was discovered in certain
service information related to the AD. The error involves an optional
threshold formula that could allow an airplane to exceed the acceptable
compliance time for addressing the unsafe condition.
We reviewed Boeing Service Bulletin 757-54-0035, Revision 6, dated
December 2, 2011. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2013-0326.
Concurrent Service Information
Boeing Service Bulletin 757-54-0035, Revision 6, dated December 2,
2011, specifies concurrent or prior accomplishment of Boeing Service
Bulletin 757-54-0003, Revision 1, dated August 30, 1985; and Boeing
Service Bulletin 757-54-0028, Revision 1, dated August 25, 1994. For
information on the procedures, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2013-0326.
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, except as discussed
under ``Differences Between the Proposed AD and the Service
Information.''
The phrase ``related investigative actions'' might be used in this
proposed AD. ``Related investigative actions'' are follow-on actions
that: (1) Are related to the primary actions, and (2) are actions that
further investigate the nature of any condition found. Related
investigative actions in an AD could include, for example, inspections.
In addition, the phrase ``corrective actions'' might be used in
this proposed AD. ``Corrective actions'' are actions that correct or
address any condition found. Corrective actions in an AD could include,
for example, repairs.
Change to Existing AD
This proposed AD would retain certain requirements of AD 2004-12-
07, Amendment 39-13666 (69 FR 33561, June 16, 2004). Since AD 2004-12-
07 was issued, the AD format has been revised, and certain paragraphs
have been rearranged. As a result, the corresponding paragraph
identifiers have changed in this proposed AD, as listed in the
following table:
Revised Paragraph Identifiers
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Requirement in AD 2004-12-07,
Amendment 39-13666 (69 FR 33561, Corresponding requirement in this
June 16, 2004) proposed AD
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paragraph (a)........................ paragraph (g)
paragraph (c)........................ paragraph (h)
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Differences Between the Proposed AD and the Service Information
Boeing Service Bulletin 757-54-0035, Revision 6, dated December 2,
2011; and Boeing Service Bulletin 757-54-0028, Revision 1, dated August
25, 1994; specify to contact the manufacturer for instructions on how
to repair certain conditions, but this proposed AD would require
repairing those conditions in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD affects 176 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Modification [retained actions Up to 1,188 work- $0 Up to $100,980 Up to $17,772,480
from AD 2004-12-07, Amendment hours x $85 per
39-13666 (69 FR 33561, June hour = $100,980.
16, 2004)].
One-time Inspection [retained 1 work-hour x $85 0 $85 $14,960
action from AD 2004-12-07, per hour = $85.
Amendment 39-13666 (69 FR
33561, June 16, 2004)].
Concurrent modification [new 142 work-hours x $85 0 $12,070 $362,100
proposed action, 30 per hour = $12,070.
airplanes].
Concurrent inspection and 104 work-hours x $85 0 $8,840 $106,080
fastener installation [new per hour = $8,840.
proposed action, 12
airplanes].
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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
[[Page 22217]]
products identified in this rulemaking action.
Regulatory Findings
We have 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 that the 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 removing airworthiness directive (AD)
2004-12-07, Amendment 39-13666 (69 FR 33561, June 16, 2004), and adding
the following new AD:
The Boeing Company: Docket No. FAA-2013-0326; Directorate Identifier
2012-NM-089-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by May 30, 2013.
(b) Affected ADs
This AD supersedes AD 2004-12-07, Amendment 39-13666 (69 FR
33561, June 16, 2004).
(c) Applicability
This AD applies to The Boeing Company Model 757-200, -200PF, and
-200CB series airplanes, certificated in any category, line numbers
1 through 735 inclusive, equipped with Rolls-Royce RB211 engines.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 54, Nacelles/Pylons.
(e) Unsafe Condition
This AD was prompted by reports indicating that the actual
operational loads applied to the nacelle are higher than the
analytical loads that were used during the initial design. We are
issuing this AD to prevent fatigue cracking in primary strut
structure and consequent reduced structural integrity of the strut.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Modification
This paragraph restates the requirements of paragraph (a) of AD
2004-12-07, Amendment 39-13666 (69 FR 33561, June 16, 2004) with new
service information. Modify the nacelle strut and wing structure
according to Boeing Service Bulletin 757-54-0035, dated July 17,
1997; Revision 1, dated April 15, 1999; Revision 2, dated June 13,
2002; or Revision 6, dated December 2, 2011; at the later of the
times specified in paragraph (g)(1) or (g)(2) of this AD, except as
required by paragraph (i) of this AD. All of the terminating actions
described in the service bulletins and listed in paragraph I.C.,
Table I, ''Strut Improvement Bulletins,'' on page 6 of Boeing
Service Bulletin 757-54-0035, dated July 17, 1997; on page 7 of
Boeing Service Bulletin 757-54-0035, Revision 1, dated April 15,
1999; and on Page 7 of Boeing Service Bulletin 757-54-0035, Revision
2, dated June 13, 2002; as applicable; must be accomplished
according to those service bulletins prior to, or concurrently with,
the accomplishment of the modification of the nacelle strut and wing
structure required by this paragraph. After July 21, 2004 (the
effective date of AD 2004-12-07), use only Boeing Service Bulletin
757-54-0035, Revision 2, dated June 13, 2002; or Boeing Service
Bulletin 757-54-0035, Revision 6, dated December 2, 2011. After the
effective date of this AD, use only Boeing Service Bulletin 757-54-
0035, Revision 6, dated December 2, 2011. Accomplishment of the
actions required by paragraph (i) of this AD terminates the
requirements of this paragraph.
(1) Prior to the accumulation of 37,500 total flight cycles, or
prior to 20 years since the date of manufacture of the airplane,
whichever occurs first.
(2) Within 3,000 flight cycles after January 3, 2000 (the
effective date of AD 99-24-07, Amendment 39-11431 (64 FR 66370,
November 26, 1999)).
(h) Retained Inspection and Repair
This paragraph restates the requirements of paragraph (c) of AD
2004-12-07, Amendment 39-13666 (69 FR 33561, June 16, 2004), with
new service information. For airplanes on which the modification
required by paragraph (g) of this AD has been done according to
Boeing Service Bulletin 757-54-0035, dated July 17, 1997: Within
15,000 flight cycles after doing the modification required by
paragraph (g) of this AD, or within 3 years after July 21, 2004 (the
effective date of AD 2004-12-07), whichever is later; do a one-time
detailed inspection of the middle gusset of the inboard side load
fitting for proper alignment, according to Part II of the
Accomplishment Instructions of Boeing Service Bulletin 757-54-0035,
Revision 1, dated April 15, 1999; or Revision 2, dated June 13,
2002, excluding Evaluation Form; or Boeing Service Bulletin 757-54-
0035, Revision 6, dated December 2, 2011. If the gusset is not
aligned properly: Before further flight, machine the gusset to the
specified angle according to the Accomplishment Instructions of
Boeing Service Bulletin 757-54-0035, Revision 1, dated April 15,
1999; or Revision 2, dated June 13, 2002, excluding Evaluation Form;
or Boeing Service Bulletin 757-54-0035, Revision 6, dated December
2, 2011. As of the effective date of this AD, use only Boeing
Service Bulletin 757-54-0035, Revision 6, dated December 2, 2011,
for accomplishing the actions required by this paragraph.
(i) New Compliance Time Limitation
For airplanes on which the modification of the nacelle strut and
wing structure required by paragraph (g) of this AD has not been
done as of the effective date of this AD: Do the modification
required by paragraph (g) of this AD at the later of the times
specified in paragraphs (i)(1) and (i)(2) of this AD.
(1) At the time specified in paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 757-54-0035, Revision 6, dated December 2,
2011, except that where this service bulletin specifies a compliance
time ``from the date on Revision 4 of this service bulletin,'' this
AD requires compliance within the specified compliance time after
the effective date of this AD.
(2) Within 3,000 flight cycles after January 3, 2000 (the
effective date of AD 99-24-07, Amendment 39-11431 (64 FR 66370,
November 26, 1999)).
(j) New Concurrent Actions
Concurrently with or prior to the accomplishment of the actions
required by paragraph (i) of this AD, do the actions specified in
paragraphs (j)(1) and (j)(2) of this AD.
(1) For airplanes identified in Boeing Service Bulletin 757-54-
0003, dated Revision 1, dated August 30, 1985: Modify the nacelle
strut upper spar, in accordance with the Accomplishment Instructions
of Boeing Service Bulletin 757-54-0003, Revision 1, dated August 30,
1985.
(2) For airplanes identified in Boeing Service Bulletin 757-54-
0028, Revision 1, dated August 25, 1994: Do a detailed inspection
and non-destructive test inspection for cracking of the lower chord,
mid-chord, and holes (for cracking, galling, corrosion, or damage
due to fastener removal), in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 757-54-0028, Revision 1,
dated August 25, 1994.
[[Page 22218]]
(k) Repair
(1) If any cracking is found during any inspection required by
paragraph (j)(2) of this AD: Before further flight, repair the
cracking using a method approved in accordance with the procedures
specified in paragraph (m) of this AD.
(2) If any holes with galling, corrosion, or damage due to
fastener removal are found during any inspection required by
paragraph (j)(2) of this AD: Before further flight, repair the
holes, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin 757-54-0028, Revision 1, dated August 25, 1994.
(l) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 757-54-0035,
Revision 4, dated June 18, 2009; or Revision 5, dated June 9, 2011;
which are not incorporated by reference in this AD.
(2) This paragraph provides credit for the actions required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 757-54-0035,
Revision 4, dated June 18, 2009; or Revision 5, dated June 9, 2011;
which are not incorporated by reference in this AD.
(3) This paragraph provides credit for the actions required by
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 757-54-0003,
dated December 14, 1984; or Boeing Service Bulletin 757-54-0028,
dated March 31, 1994; which are not incorporated by reference in
this AD.
(m) 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 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.
(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.
(n) 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:
[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; phone: 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, WA. For information on the availability of
this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on April 4, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-08768 Filed 4-12-13; 8:45 am]
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