[Federal Register Volume 81, Number 62 (Thursday, March 31, 2016)]
[Rules and Regulations]
[Pages 18456-18460]
[FR Doc No: 2016-07024]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3983; Directorate Identifier 2015-NM-141-AD;
Amendment 39-18448; AD 2016-07-03]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B,
747-300, 747SR, and 747SP series airplanes. This AD was prompted by an
evaluation by the design approval holder (DAH) indicating that the
upper chords of the upper deck floor beams are subject to widespread
fatigue damage (WFD). This AD requires repetitive inspections for
cracks at the floor panel attachment fastener holes; repetitive
inspections for cracks in the upper and lower chords of the upper deck
floor beams at permanent fastener locations; repetitive inspections for
cracks in certain repaired and modified areas; and related
investigative and corrective actions if necessary. This AD also
requires repetitive replacement of the upper chords of the upper deck
floor beams, including pre-replacement inspections and corrective
action if necessary; and post-replacement repetitive inspections and
repair if necessary. We are issuing this AD to detect and correct
fatigue cracking of the upper chords of the upper deck floor beams.
Undetected cracking could result in large deflection or deformation of
the upper deck floor beams, resulting in damage to wire bundles and
control cables for the flight control system, and reduced
controllability of the airplane. Multiple adjacent severed floor beams
could result in rapid decompression of the airplane.

DATES: This AD is effective May 5, 2016.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 5, 2016.

ADDRESSES: For service information identified in this final rule,
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<PHONE_NUMBER>; 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<PHONE_NUMBER>. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3983.

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-2015-
3983; 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: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA

98057-3356; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>
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 certain The Boeing Company
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SR, and
747SP series airplanes. The NPRM published in the Federal Register on
October 6, 2015 (80 FR 60303) (``the NPRM''). The NPRM was prompted by
an evaluation by the DAH indicating that the upper chords of the upper
deck floor beams are subject to WFD. The NPRM proposed to require
repetitive inspections for cracks at the floor panel attachment
fastener holes; repetitive inspections for cracks in the upper and
lower chords of the upper deck floor beams at permanent fastener
locations; repetitive inspections for cracks in certain repaired and
modified areas; and related investigative and corrective actions if
necessary. The NPRM also proposed to require repetitive replacement of
the upper chords of the upper deck floor beams, including pre-
replacement inspections and corrective action if necessary; and post-
replacement repetitive inspections and repair if necessary. We are
issuing this AD to detect and correct fatigue cracking of the upper
chords of the upper deck floor beams. Undetected cracking could result
in large deflection or deformation of the upper deck floor beams,
resulting in damage to wire bundles and control cables for the flight
control system, and reduced controllability of the airplane. Multiple
adjacent severed floor beams could result in rapid decompression of the
airplane.

Comments

    We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment. A member of the public supported
the NPRM and an anonymous commenter had no objection to the NPRM.

Request To Clarify Credit for Previous Actions

    Boeing requested that we clarify that credit for previous actions
is limited to those actions that comply with the new proposed
requirements of the NPRM. Boeing noted that paragraph (m) of the
proposed AD should provide credit for using Boeing Alert Service
Bulletin 747-53A2452, dated April 3, 2003, provided the new
requirements specified in Boeing Alert Service Bulletin 747-53A2452,
Revision 1, dated July 16, 2012, are met.
    We agree that clarification is necessary. Paragraph (m) of this AD,
``Credit for Previous Actions,'' provides credit for actions done
before the effective date of this AD using Boeing Alert Service
Bulletin 747-53A2452, dated April 3, 2003, for the corresponding
actions required by paragraphs (g), (h), and (i) of this AD. Paragraphs
(g), (h), and (i) of this AD refer to Boeing Alert Service Bulletin
747-53A2452, Revision 1, dated July 16, 2012, as the appropriate source
of service information for accomplishing the actions required by those
paragraphs. Boeing Alert Service Bulletin 747-53A2452, Revision 1,
dated July 16, 2012, added certain inspection locations. Therefore, for
the added inspection locations specified in Boeing Alert Service
Bulletin 747-53A2452, Revision 1, dated July 16, 2012, paragraph (m) of
this AD does not provide credit because Boeing Alert Service Bulletin
747-53A2452, dated April 3, 2003, cannot be used for those locations.
We have revised paragraph (m) of this AD to clarify that although
credit is given for using Boeing Alert Service Bulletin 747-53A2452,
dated April 3, 2003, actions required by paragraphs (g), (h), and (i)
of this AD that are not identified in Boeing Alert Service Bulletin
747-53A2452, dated April 3, 2003, must still be done.
    Boeing also stated that credit should be given in the NPRM for
Boeing Alert Service Bulletin 747-53A2452, Revision 1, dated July 16,
2012; and Boeing Alert Service Bulletin 747-53A2852, dated June 22,
2012.
    We have not included Boeing Alert Service Bulletin 747-53A2452,
Revision 1, dated July 16, 2012; and Boeing Alert Service Bulletin 747-
53A2852, dated June 22, 2012; in paragraph (m) of this AD because that
service information is already cited in paragraphs (g) through (k) of
this AD as the only appropriate source of service information for
accomplishing the actions required by this AD. As allowed by the
phrase, ``unless already done,'' in paragraph (f) of this AD, if the
requirements of this AD have already been accomplished, this AD does
not require that those actions be repeated.

Request To Give Credit for Previous Alternative Methods of Compliance
(AMOCs)

    Boeing requested that previously approved AMOCs for AD 2005-20-29,
Amendment 39-14326 (70 FR 59246, October 12, 2005), be approved for the
corresponding provisions of the proposed AD, provided the previously
approved AMOCs satisfy the inspection locations and compliance times
specified by the proposed AD. Boeing noted that AMOCs would be needed
for new inspection locations and compliance times specified in the
proposed AD.
    We acknowledge that certain AMOCs for AD 2005-20-29, Amendment 39-
14326 (70 FR 59246, October 12, 2005), might also address the actions
and compliance times required by this AD. However, each individual AMOC
would need to be evaluated to ensure the identified unsafe condition is
addressed. Any person may request approval of an AMOC under the
provisions of paragraph (o) of this AD. We have not changed 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:
     [Agr]re consistent with the intent that was proposed in
the NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.
    We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information.
     Boeing Alert Service Bulletin 747-53A2452, Revision 1,
dated July 16, 2012. This service information describes procedures for
repetitive open hole or surface high frequency eddy current (HFEC)
inspections, as applicable, for cracks at the floor panel attachment
fastener holes in certain areas and stations; repetitive surface HFEC
inspections for cracks in the upper and lower chords of the upper deck
floor beams at permanent fastener locations in certain areas and
stations; and related investigative and corrective actions. This
service information also describes procedures, for airplanes on which
certain repairs or modifications are done, for repetitive open hole or
surface HFEC inspections, as applicable, for cracks in the repaired and
modified areas; and repair.
     Boeing Alert Service Bulletin 747-53A2852, dated June 22,
2012. This

service information describes procedures for repetitive replacement of
the upper chords of the upper deck floor beams, including pre-
replacement inspections and corrective action, and post-replacement
repetitive inspections and repair.
    This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 67 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
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                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
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Inspections specified in Boeing    Up to 884 work-                  $0  $75,140, per         $5,034,380, per
 Alert Service Bulletin             hours x $85 per                      inspection cycle.    inspection cycle.
 747[dash]53A2452, Revision 1,      hour = $75,140,
 dated July 16, 2012.               per inspection
                                    cycle.
Replacement specified in Boeing    Up to 696 work-              \1\ $0  $59,160, per         $3,963,720, per
 Alert Service Bulletin             hours x $85 per                      replacement.         replacement.
 747[dash]53A2852, dated June 22,   hour = $59,160,
 2012.                              per replacement.
Post-replacement inspections       Up to 586 work-                  $0  $49,810, per         $3,337,270, per
 specified in Boeing Alert          hours x $85 per                      inspection cycle.    inspection cycle.
 Service Bulletin                   hour = $49,810,
 747[dash]53A2852, dated June 22,   per inspection
 2012.                              cycle.
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\1\ We currently have no specific cost estimates associated with the parts necessary for the replacement.

    We have received no definitive data that would enable us to provide
cost estimates for the on-condition 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

    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):

2016-07-03 The Boeing Company: Amendment 39-18448 ; Docket No. FAA-
2015-3983; Directorate Identifier 2015-NM-141-AD.

(a) Effective Date

    This AD is effective May 5, 2016.

(b) Affected ADs

    This AD affects AD 2005-20-29, Amendment 39-14326 (70 FR 59246,
October 12, 2005).

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-300, 747SR, and 747SP series airplanes;
certificated in any category; as identified in Boeing Alert Service
Bulletin 747-53A2852, dated June 22, 2012.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the upper chords of the upper deck
floor beams are subject to widespread fatigue damage (WFD). We are
issuing this AD to detect and correct fatigue cracking of the upper
chords of the upper deck floor beams. Undetected cracking could
result in large deflection or deformation of the upper deck floor
beams, resulting in damage to wire bundles and control cables for
the flight control system, and reduced controllability of the
airplane. Multiple adjacent severed floor beams could result in
rapid decompression of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Repetitive Inspections of the Upper Chords of the Upper Deck Floor
Beams

    At the applicable times specified in Tables 1 through 7 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2452, Revision 1, dated July 16, 2012, except as required by
paragraph (l)(1) of this AD: Do the inspections specified in
paragraphs (g)(1) and (g)(2) of this AD, and do all applicable
related investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2452, Revision 1, dated July 16, 2012, except as required by
paragraph (l)(2) of this AD. Repeat the inspections specified in
paragraphs (g)(1) and (g)(2) of this AD thereafter at the applicable

times specified in Tables 1 through 7 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2452,
Revision 1, dated July 16, 2012. Do all applicable related
investigative and corrective actions before further flight. Doing
the inspections required by paragraphs (g)(1) and (g)(2) of this AD
terminates the inspections required by paragraphs (m) and (n) of AD
2005-20-29, Amendment 39-14326 (70 FR 59246, October 12, 2005).
    (1) Do an open hole or surface high frequency eddy current
(HFEC) inspection, as applicable, for cracks at the fastener holes
of the floor panel attachment in the applicable areas and stations
identified in Boeing Alert Service Bulletin 747-53A2452, Revision 1,
dated July 16, 2012.
    (2) Do a surface HFEC inspection for cracks in the upper and
lower chords of the upper deck floor beams at permanent fastener
locations in the applicable areas and stations identified in Boeing
Alert Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012.

(h) Terminating Modification and Repair for the Inspection Specified in
Paragraph (g)(1) of This AD

    A fastener hole modification or a fastener hole repair in Area 1
or Area 2 as described in Boeing Alert Service Bulletin 747-53A2452,
Revision 1, dated July 16, 2012, terminates the inspection of the
fastener holes of the floor panel attachment required by paragraph
(g)(1) of this AD for the repaired or modified area only, provided
the modification and repair, including related investigative and
corrective actions, are done in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2452, Revision
1, dated July 16, 2012, except as required by paragraph (l)(2) of
this AD.

(i) Post Modification/Repair Repetitive Inspections

    (1) For airplanes on which any fastener hole modification or any
fastener hole repair was done as specified in Boeing Alert Service
Bulletin 747-53A2452: Except as required by paragraph (i)(2) of this
AD, at the applicable times specified in Tables 8 and 9 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2452,
Revision 1, dated July 16, 2012, or within 1,000 flight cycles after
the effective date of this AD, whichever occurs later, do an open
hole or surface HFEC inspection, as applicable, for cracks in the
repaired and modified areas, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2452, Revision
1, dated July 16, 2012. If any cracking is found, before further
flight, repair using a method approved in accordance with the
procedures specified in paragraph (o) of this AD. Repeat the
applicable inspections thereafter at the times specified in Tables 8
and 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 747-53A2452, Revision 1, dated July 16, 2012. Doing an
inspection required by this paragraph terminates the inspections
required by paragraph (p) of AD 2005-20-29, Amendment 39-14326 (70
FR 59246, October 12, 2005).
    (2) For any repair #10 or repair #13 done as specified in Boeing
Alert Service Bulletin 747-53A2452: Before further flight, do post-
repair inspections using a method approved in accordance with the
procedures specified in paragraph (o) of this AD.

(j) Replacement of the Upper Chords of the Upper Deck Floor Beams
(Includes Pre-Replacement Inspections)

    Replace the upper chords of the upper deck floor beams by doing
the actions required by paragraphs (j)(1) and (j)(2) of this AD at
the times specified in those paragraphs. Accomplishing the
replacement required by this paragraph terminates the inspections
required by paragraphs (g) and (i) of this AD.
    (1) Before the accumulation of 30,000 total flight cycles, or
within 3,000 flight cycles after the effective date of this AD,
whichever occurs later, do an open hole HFEC inspection for cracks
at certain fastener locations in the floor beam webs and side of
body frames, and do a detailed inspection for cracks of any removed
part that will be re-installed, and do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2852, dated June 22, 2012,
except as required by paragraph (l)(2) of this AD. Do all applicable
corrective actions before further flight.
    (2) Before further flight after accomplishing the inspections
required by paragraph (j)(1) of this AD, install new upper chords of
the upper deck floor beams and reinforcing straps or angles, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2852, dated June 22, 2012, except as
required by paragraph (l)(2) of this AD.

(k) Post-Replacement Repetitive Inspections

    For airplanes on which any replacement required by paragraph (j)
or (k)(2)(ii) of this AD is done: At the applicable times specified
in Tables 2 through 4 in paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 747-53A2852, dated June 22, 2012, do HFEC
inspections for cracks at the permanent fastener holes and the upper
chords of the upper deck floor beams, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2452, Revision 1, dated July 16, 2012.
    (1) If any cracking is found during any inspection required by
the introductory text of paragraph (k) or paragraph (k)(2)(i) of
this AD, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD.
    (2) If no cracking is found during any inspection required by
the introductory text of paragraph (k) or paragraph (k)(2)(i) of
this AD, do the actions required by paragraphs (k)(2)(i) and
(k)(2)(ii) of this AD.
    (i) Repeat the inspections specified in paragraph (k) of this AD
thereafter at the applicable times specified in Tables 8 and 9 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2452, Revision 1, dated July 16, 2012.
    (ii) Within 10,000 flight cycles after accomplishing the initial
HFEC inspections required by the introductory text of paragraph (k)
of this AD, replace the upper chords of the upper deck floor beams
by doing the actions specified in paragraphs (j)(1) and (j)(2) of
this AD.

(l) Exceptions to Service Information

    (1) Where Boeing Alert Service Bulletin 747-53A2452, Revision 1,
dated July 16, 2012, specifies a compliance time ``after the
Revision 1 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
    (2) Where Boeing Alert Service Bulletin 747-53A2452, Revision 1,
dated July 16, 2012; or Boeing Alert Service Bulletin 747-53A2852,
dated June 22, 2012; specifies to contact Boeing for appropriate
action: Before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD.

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by
paragraphs (g), (h), and (i) of this AD, if those actions were
performed before the effective date of this AD using Boeing Alert
Service Bulletin 747-53A2452, dated April 3, 2003. For the actions
required by paragraphs (g), (h), and (i) of this AD that are not
identified in Boeing Alert Service Bulletin 747-53A2452, dated April
3, 2003, those actions must still be done. Boeing Alert Service
Bulletin 747-53A2452, dated April 3, 2003, is incorporated by
reference in AD 2005-20-29, Amendment 39-14326 (70 FR 59246, October
12, 2005).

(n) 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.

(o) 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 (p) of this AD.
Information may be emailed to<EMAIL_ADDRESS>    (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, modification, or alteration 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. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.

(p) Related Information

    (1) For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>    (2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (q)(3) and (q)(4) of this AD.

(q) 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 747-53A2452, Revision 1, dated
July 16, 2012.
    (ii) Boeing Alert Service Bulletin 747-53A2852, dated June 22,
2012.
    (3) 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<PHONE_NUMBER>; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at 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.
    (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<PHONE_NUMBER>, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 20, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-07024 Filed 3-30-16; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register: February 17, 2009 (Volume 74, Number 30)]
[Proposed Rules]
[Page 7384-7385]
[DOCID:fr17fe09-14]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0035; Directorate Identifier 2008-NM-096-AD]
RIN 2120-AA64

Airworthiness Directives; Saab Model 340A (SAAB/SF340A) and SAAB
340B 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 the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:

    Field experiences have revealed cracks in the frames and closing
angle on the forward engine cowl door * * *.
    In case of a damaged frame and/or closing angle, the forward
engine cowl door can loosen during flight and depart from the
aircraft.
* * * * *

The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by March 19, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact
Saab Aircraft AB, SAAB Aerosystems, SE-581 88, Link[ouml]ping, Sweden;
telephone +46 13 18 5591; fax +46 13 18 4874; e-mail
<EMAIL_ADDRESS>Internet http://www.saabgroup.com.
You may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the
FAA, call<PHONE_NUMBER> or<PHONE_NUMBER>.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone<PHONE_NUMBER>) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace
Engineer, International Branch, ANM-116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356;
telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.

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-2009-0035;
Directorate Identifier 2008-NM-096-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 based on 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

    The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2008-0069, dated April 11, 2008 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:

    Field experiences have revealed cracks in the frames and closing
angle on the forward engine cowl door NS STA [nacelle station] 203
and 250.
    In case of a damaged frame and/or closing angle, the forward
engine cowl door can loosen during flight and depart from the
aircraft.
    This AD is issued to require a detailed inspection to find out
if there are any cracks [or deformations or wear damage] in the
frames and/or the closing angles. The inspection is on four points
on each of the forward engine cowl doors.

The corrective action depends on if the crack, deformation, or wear
damage is within or outside certain defined limits, and includes
doing a repair either in accordance with the specified service
information, or contacting Saab for repair instructions and doing
the repair. You may obtain further information by examining the MCAI
in the AD docket.

Relevant Service Information

    Saab has issued Service Bulletin 340-71-060, dated February 8,
2008. The actions described in this service information are intended
to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of
another country, and is approved for operation in the United States.
Pursuant to our bilateral agreement with the State of Design
Authority, we have been notified of the unsafe condition described
in the MCAI and service information referenced above. We are
proposing this AD because we evaluated all pertinent information and
determined an unsafe condition exists and is likely to exist or
develop on other products of the same type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD
would affect 141 products of U.S. registry. We also estimate that it
would take 2 work-

hours per product to comply with the basic requirements of this
proposed AD. The average labor rate is $80 per work-hour. Based on
these figures, we estimate the cost of the proposed AD on U.S.
operators to be $22,560, or $160 per product.

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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:
Saab Aircraft AB: Docket No. FAA-2009-0035; Directorate Identifier
2008-NM-096-AD.

Comments Due Date

    (a) We must receive comments by March 19, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Saab Model 340A (SAAB/SF340A) airplanes,
serial numbers (S/Ns) 004 thorough 159 inclusive, and Model SAAB
340B airplanes, S/Ns 160 through 459 inclusive; certificated in any
category.

Subject

    (d) Air Transport Association (ATA) of America Code 71: Power
Plant.

Reason

    (e) The mandatory continuing airworthiness information (MCAI)
states:

    Field experiences have revealed cracks in the frames and closing
angle on the forward engine cowl door NS STA [nacelle station] 203
and 250.
    In case of a damaged frame and/or closing angle, the forward
engine cowl door can loosen during flight and depart from the
aircraft.
    This AD is issued to require a detailed inspection to find out
if there are any cracks [or deformations or wear damage] in the
frames and/or the closing angles. The inspection is on four points
on each of the forward engine cowl doors.
    The corrective action depends on if the crack, deformation, or
wear damage is within or outside certain defined limits, and
includes doing a repair either in accordance with the specified
service information, or contacting Saab for repair instructions and
doing the repair.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 1,000 flight hours after the effective date of this
AD, do a detailed inspection for cracking, deformation, or wear
damage of the frame and closing angle on the forward engine cowl
door, in accordance with the Accomplishment Instructions of Saab
Service Bulletin 340-71-060, dated February 8, 2008.
    (2) If any crack, deformation, or wear damage is found during
the inspection required by paragraph (f)(1) of this AD, before
further flight, do all applicable corrective actions in accordance
with the Accomplishment Instructions of Saab Service Bulletin 340-
71-060, dated February 8, 2008.
    (3) Submit a report of the findings of the inspection required
by paragraph (f)(1) of this AD to Saab at the address specified in
Saab Service Bulletin 340-71-060, dated February 8, 2008. Submit the
report at the applicable time specified in paragraph (f)(3)(i) or
(f)(3)(ii) of this AD. The report must include the information
specified in the ``Inspection Result Formula'' form in the service
bulletin.
    (i) If the inspection was done after the effective date of this
AD: Submit the report within 30 days after the inspection.
    (ii) If the inspection was accomplished before the effective
date of this AD: Submit the report within 30 days after the
effective date of this AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN:
Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone<PHONE_NUMBER>; fax (425)
227-1149. Before using any approved AMOC on any airplane to which
the AMOC applies, notify your appropriate principal inspector (PI)
in the FAA Flight Standards District Office (FSDO), or lacking a PI,
your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency (EASA)
Airworthiness Directive 2008-0069, dated April 11, 2008, and Saab
Service Bulletin 340-71-060, dated February 8, 2008, for related
information.

    Issued in Renton, Washington, on January 9, 2009.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
 [FR Doc. E9-3264 Filed 2-13-09; 8:45 am]

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