[Federal Register Volume 79, Number 219 (Thursday, November 13, 2014)]
[Proposed Rules]
[Pages 67379-67382]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-26837]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0756; Directorate Identifier 2014-NM-103-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 707 airplanes, and Model 720 and 720B series
airplanes. This proposed AD is intended to complete certain mandated
programs intended to support the airplane reaching its limit of
validity (LOV) of the engineering data that support the established
structural maintenance program. This proposed AD would require
repetitive inspections for cracking of the inboard and outboard midspar
fittings of the nacelle struts and of the torque bulkhead, midspar
chords, drag fitting, and front spar support, and doing applicable
related investigative and corrective actions; replacing the midspar
fittings; and doing other specified actions. We are proposing this AD
to detect and correct cracking in the midspar fittings of the inboard
and outboard nacelle struts, which could result in the loss of the
structural integrity of the midspar fitting. This condition could cause
an unsafe separation of the engine and consequent wing fire.
DATES: We must receive comments on this proposed AD by December 29,
2014.
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 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 view this 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 by searching for and locating Docket No. FAA-2014-
0756; 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: Chandra Ramdoss, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5239; fax: 562-627-5210; 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-2014-0756;
Directorate Identifier 2014-NM-103-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
As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs
have been developed to support initiatives that will ensure the
continued airworthiness of aging airplane structure. The last element
of those initiatives is the requirement to establish a limit of
validity (LOV) of the engineering data that support the structural
maintenance program under 14 CFR 26.21. This proposed AD is the result
of an assessment of the previously established programs by Boeing
during the process of establishing the LOV for Model 707 airplanes and
Model 720 and 720B series airplanes. The actions specified in this
proposed AD are necessary to complete certain programs to ensure the
continued airworthiness of aging airplane structure and to support an
airplane reaching its LOV.
We received reports of cracked midspar fittings on the inboard and
outboard nacelle struts. The airplanes had accumulated between 9,900
and 63,000 total flight hours. Five of these airplanes had cracked
midspar fittings that resulted in separation of the inboard strut and
engine from the airplane inflight. In two of those events the inboard
nacelle strut contacted the outboard engine, causing it to separate
from the airplane. Operators have also reported cracking in the
transition radius of the inboard and outboard midspar fittings of the
nacelle struts of the numbers 1 and 4 engines.
The reported cracks on the inboard and outboard midspar fittings of
the nacelle struts of engines numbers 1, 2, 3, and 4 were found to be
vertical at the
[[Page 67380]]
lug hole or across the double horizontal tangs at the radius where the
tangs merge with the lug. Analysis determined that the 4330 steel
midspar fittings cracked as a result of stress corrosion and fatigue at
the lug and fatigue at the tangs.
Cracked midspar fittings, if not detected and corrected, could
result in the loss of the structural integrity of the midspar fitting.
This condition could cause an unsafe separation of the engine and
consequent wing fire.
Relevant Service Information
We reviewed Boeing 707 Alert Service Bulletin A3183, Revision 6,
dated February 7, 2014. For information on the procedures and
compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0756.
Related Rulemaking
AD 93-11-02, Amendment 39-8594, Docket No. 92-NM-230-AD, which
applies to The Boeing Company Model 707 and 720 series airplanes,
requires repetitive inspections for cracking of the midspar fittings on
the inboard struts, related investigative and corrective actions if
necessary, and replacement of the midspar fittings with new, improved
fittings, which constitutes terminating action for the repetitive
inspections.
AD 2012-16-12, Amendment 39-17159 (77 FR 49708, August 17, 2012),
which applies to The Boeing Company Model 707 airplanes, and Model 720
and 720B series airplanes, requires a detailed inspection of the
midspar fittings of the nacelle struts for engine numbers 2 and 3 to
confirm that the correct part number is installed, and installing the
correct part number if it is not installed. The correct part number is
the new, improved midspar fitting required by AD 93-11-02, Amendment
39-8594, Docket No. 92-NM-230-AD. AD 2012-16-12 also requires
repetitive high frequency eddy current inspections (HFEC) of the
midspar fittings of engine numbers 2 and 3 nacelle struts for cracks
and repair if necessary. In addition, AD 2012-16-12 requires repetitive
general visual inspections of the nacelle struts of engine numbers 1,
2, 3, and 4 to verify that the nacelle strut has not drooped below its
normal position, and repair if necessary.
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 inspections for
cracking of the inboard and outboard midspar fittings of the nacelle
struts and of the torque bulkhead, midspar chords, drag fitting, and
front spar support, and doing applicable related investigative and
corrective actions; replacing the midspar fittings; and doing other
specified actions; as specified in parts 2 through 6, inclusive, of the
Accomplishment Instructions of the service information described
previously, except as discussed under ``Differences Between this
Proposed AD and the Service Information.''
The phrase ``related investigative actions'' is used in this
proposed AD. ``Related investigative actions'' are follow-on actions
that (1) are related to the primary actions, and (2) further
investigate the nature of any condition found. Related investigative
actions in an AD could include, for example, inspections.
The phrase ``corrective actions'' is 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.
The phrase ``other specified actions'' is used in this proposed AD.
Other specified actions in this proposed AD include installing new
inboard and outboard midspar fittings, installing oversized fasteners
in the two forward most fastener holes common to the inboard side of
the nacelle strut overwing support fitting and the wing front spar
upper chord, applying sealant to the midspar area, and applying
corrosion inhibiting compound to the midspar fitting areas.
We have determined that the actions specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin
A3183, Revision 6, dated February 7, 2014, should not be required in
this AD, as noted in the service bulletin.
Differences Between This Proposed AD and the Service Information
Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February
7, 2014, specifies to contact the manufacturer for fitting installation
instructions and instructions on how to repair certain conditions, but
this proposed AD would require doing those corrective actions 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 12 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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Inspections....................... 214 work-hours x $85 per $0.......................... $18,190..................... $218,280.
hour = $18,190 per
inspection cycle.
Replacement of midspar fitting.... 18 work-hours x $85 per Up to $7,867................ Up to $9,397................ Up to $112,764.
hour = $1,530.
Mid-interval inspections.......... 107 work-hours x $85 per $0.......................... $9,095...................... $109,140.
hour = $9,095 per
inspection cycle.
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We estimate the following costs to do any additional inspections
that would be required based on the results of the proposed
inspections. We have no way of determining the number of aircraft that
might need these inspections:
[[Page 67381]]
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Inspections............................... Up to 21 work-hours x $85 per hour $0 $1,785
= $1,785.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition corrective actions specified in
this AD.
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-2014-0756; Directorate
Identifier 2014-NM-103-AD.
(a) Comments Due Date
We must receive comments by December 29, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 707-100 long
body, -200, -100B long body, and -100B short body series airplanes;
Model 707-300, -300B, -300C, and -400 series airplanes; and Model
720 and 720B series airplanes; certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.
(e) Unsafe Condition
This AD was prompted by certain mandated programs intended to
support the airplane reaching its limit of validity (LOV) of the
engineering data that support the established structural maintenance
program. We are issuing this AD to detect and correct cracking in
the midspar fittings of the inboard and outboard nacelle struts,
which could result in the loss of the structural integrity of the
midspar fitting. This condition could cause an unsafe separation of
the engine and consequent engine fire.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections of Nacelle Struts and Surrounding Structure and
Replacement of Inboard and Outboard Midspar Fittings
At the applicable time specified in table 2 or table 3 of
paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin
A3183, Revision 6, dated February 7, 2014, except as required by
paragraph (i)(1) of this AD: Do the inspections required by
paragraphs (g)(1), (g)(2), and (g)(3) of this AD in accordance with
part 2 or part 3, as applicable, of the Accomplishment Instructions
of Boeing Alert Service Bulletin A3183, Revision 6, dated February
7, 2014, except as required by paragraph (i)(2) of this AD. Before
further flight, do all applicable related investigative and
corrective actions, replace the inboard and outboard midspar
fittings with new parts, and do other specified actions (including
installing new bushings and oversize fasteners) in accordance with
part 2 or part 3, as applicable, of the Accomplishment Instructions
of Boeing Alert Service Bulletin A3183, Revision 6, dated February
7, 2014, except as required by paragraph (i)(2) of this AD. Repeat
the inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of
this AD thereafter at the applicable intervals specified in table 2
or table 3 of paragraph 1.E., ``Compliance,'' of Boeing 707 Alert
Service Bulletin A3183, Revision 6, dated February 7, 2014, except
as required by paragraph (i)(1) of this AD.
(1) A detailed inspection and a high frequency eddy current
inspection (HFEC) for cracks in the inboard and outboard midspar
fittings of the nacelle struts.
(2) Open hole HFEC inspections for cracks in the torque
bulkhead, midspar chords, drag fitting, and front spar support.
(3) A surface HFEC inspection of the front spar support for
cracks.
(h) Mid-Interval Inspections and Replacement of Nacelle Strut Midspar
Fittings
At the applicable time specified in table 4 or 5 of paragraph
1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin A3183,
Revision 6, dated February 7, 2014: Do the inspections required by
paragraphs (h)(1), (h)(2), and (h)(3) of this AD, in accordance with
part 4 or part 5, as applicable, of the Accomplishment Instructions
of Boeing Alert Service Bulletin A3183, Revision 6, dated February
7, 2014, except as required by paragraph (i)(2) of this AD. Do all
applicable related investigative, corrective, and other specified
actions (including installing new bushings and oversize fasteners)
before further flight. Repeat the inspections required by paragraphs
(h)(1), (h)(2), and (h)(3) of this AD thereafter at the applicable
intervals specified in table 4 or 5 of paragraph 1.E.,
``Compliance,'' of Boeing 707 Alert Service Bulletin A3183, Revision
6, dated February 7, 2014. The threshold for the repetitive
inspections required by paragraphs (h)(1), (h)(2), and (h)(3) of
this AD is 1,500 flight cycles or 48 months, whichever occurs first,
since the most recent midspar fitting replacement.
(1) A detailed inspection and a surface HFEC inspection for
cracks in the inboard
[[Page 67382]]
and outboard midspar fittings of the nacelle struts.
(2) An open hole HFEC inspection for cracks in the drag fitting
and front spar support.
(3) A surface HFEC inspection for cracks in the front spar
support.
(i) Exceptions to Service Information Specifications
(1) Where Boeing 707 Alert Service Bulletin A3183, Revision 6,
dated February 7, 2014, specifies a compliance time ``after the
Revision 6 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where Boeing 707 Alert Service Bulletin A3183, Revision 6,
dated February 7, 2014, specifies to contact Boeing for appropriate
action: Do corrective actions before further flight using a method
approved in accordance with the procedures specified in paragraph
(k) of this AD.
(j) Special Flight Permit
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office, 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: [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, Los Angeles 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 Chandra Ramdoss,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office (ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210;
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 view this 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 November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-26837 Filed 11-12-14; 8:45 am]
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