[Federal Register Volume 81, Number 174 (Thursday, September 8, 2016)]
[Proposed Rules]
[Pages 62031-62035]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-21147]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9067; Directorate Identifier 2016-NM-043-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 747-100, 747-100B, 747-100B SUD, 747-200B,
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and
747SP series airplanes. This proposed AD was prompted by a report of
incidents involving fatigue cracking in transport category airplanes
that are approaching or have exceeded their design service objective
and a structural reevaluation by the manufacturer that identified
additional structural elements that qualify as structural significant
items (SSIs). This proposed AD would require revising the maintenance
or inspection program, as applicable, to include inspections that will
give no less than the required damage tolerance rating (DTR) for
certain SSIs, and repairing any cracked structure. This proposed AD
would also require inspections to detect cracks of all SSI structure,
and repair if necessary. We are proposing this AD to ensure the
continued structural integrity of all The Boeing Company Model 747-100,
747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes.
DATES: We must receive comments on this proposed AD by October 24,
2016.
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 NPRM, 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-2016-
9067; 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
[[Page 62032]]
(phone: 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; 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-2016-9067;
Directorate Identifier 2016-NM-043-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 December 26, 2007, we issued AD 2004-07-22 R1, Amendment 39-
15326 (73 FR 1052, January 7, 2008); corrected February 14, 2008 (73 FR
8589) (``AD 2004-07-22 R1''); for all The Boeing Company Model 747-100,
747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2004-07-22 R1
requires that the maintenance inspection program be revised to include
inspections that will give no less than the required DTR for each SSI,
and repair of cracked structure. AD 2004-07-22 R1 was prompted by a
report of incidents involving fatigue cracking in transport category
airplanes that are approaching or have exceeded their design service
objective. We issued AD 2004-07-22 R1 to ensure the continued
structural integrity of all Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-
400F, 747SR, and 747SP series airplanes.
Actions Since AD 2004-07-22 R1 Was Issued
Since we issued AD 2004-07-22 R1, a structural reevaluation by the
manufacturer identified additional structural elements that qualify as
SSIs. We have determined that supplemental inspections are required for
timely detection of fatigue cracking for these additional structural
elements.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Document No. D6-35022, ``Supplemental Structural
Inspection Document for Model 747 Airplanes,'' Revision H, dated
September 2013. The service information describes procedures for
inspections to detect cracks of all structure identified as SSIs and
includes six new SSIs since the last revision.
We also reviewed Boeing Document No. D6-35022-1, ``747-400 LCF
Supplemental Structural Inspection Document--Appendix A,'' dated
November 2015. The service information describes procedures for
inspections of wing, fuselage, and empennage SSIs for Model 747-400 LCF
airplanes.
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.
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 revising the maintenance or
inspection program, as applicable, to include inspections that will
give no less than the required DTR for certain SSIs, and repairing any
cracked structure. This proposed AD would also require inspections to
detect cracks of all SSI structure, and repair if necessary.
This proposed AD does not supersede 2004-07-22 R1. However,
accomplishing the revision specified in paragraph (h) of this proposed
AD would terminate the requirements of paragraphs (f), (g), and (h) of
AD 2004-07-22 R1. Also, doing an inspection specified in paragraph (i)
of this proposed AD would terminate the corresponding inspection
required by paragraph (i) of AD 2004-07-22 R1.
Costs of Compliance
We estimate that this proposed AD affects 118 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Revision of maintenance or 1 work-hour x $85 per $0 $85 $10,030
inspection program. hour = $85.
----------------------------------------------------------------------------------------------------------------
We have not specified cost estimates for the inspection and repair
specified in this proposed AD. Compliance with this proposed AD
constitutes a method of compliance with the FAA aging airplane safety
final rule (AASFR) (70 FR 5518, February 2, 2005) for certain baseline
structure of Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C,
747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series
airplanes. The AASFR requires certain operators to incorporate damage
tolerance inspections into their maintenance inspection programs. These
requirements are described in 14 CFR 121.1109(c)(1) and 14 CFR
129.109(b)(1). Accomplishment of the actions specified in this proposed
AD will meet the requirements of these regulations for certain baseline
structure. The costs for accomplishing the inspection portion of this
proposed AD were accounted for in the regulatory evaluation of the
AASFR.
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.
[[Page 62033]]
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-2016-9067; Directorate Identifier
2016-NM-043-AD.
(a) Comments Due Date
We must receive comments by October 24, 2016.
(b) Affected ADs
This AD affects AD 2004-07-22 R1, Amendment 39-15326 (73 FR
1052, January 7, 2008); corrected February 14, 2008 (73 FR 8589)
(``AD 2004-07-22 R1'').
(c) Applicability
This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated
in any category.
Note 1 to paragraph (c) of this AD: A Model 747-400 LCF airplane
is a Model 747-400 series airplane that has been modified from a
passenger airplane to a freighter configuration as specified in
Boeing Service Bulletin 747-00-2084.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage;
54, Nacelles/Pylons; 55, Stabilizers; 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of incidents involving fatigue
cracking in transport category airplanes that are approaching or
have exceeded their design service objective and a structural
reevaluation by the manufacturer that identified additional
structural elements that qualify as structural significant items
(SSIs). We are issuing this AD to ensure the continued structural
integrity of all The Boeing Company Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, 747SR, and 747SP series airplanes.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definition of SSI
For the purposes of this AD, an SSI is defined as a principal
structural element (PSE). A PSE is a structural element that
contributes significantly to the carrying of flight, ground, or
pressurization loads, and whose integrity is essential in
maintaining the overall structural integrity of the airplane.
(h) Maintenance or Inspection Program Revision for All Airplanes
Prior to reaching the compliance thresholds specified in
paragraph (i)(1)(i), (i)(2)(i), (j)(1)(i), or (j)(2)(i) of this AD,
as applicable, or within 12 months after the effective date of this
AD, whichever occurs later: Incorporate a revision into the
maintenance or inspection program, as applicable, that provides no
less than the required damage tolerance rating (DTR) for each SSI
listed in the applicable service information specified in paragraph
(h)(1) or (h)(2) of this AD. The revision to the maintenance or
inspection program must include, and must be implemented in
accordance with, the procedures in Section 5.0, ``Damage Tolerance
Rating (DTR) System Application,'' of Boeing Document No. D6-35022,
``Supplemental Structural Inspection Document for Model 747
Airplanes,'' Revision H, dated September 2013; and Boeing Document
No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection
Document--Appendix A,'' dated November 2015; as applicable.
Accomplishing the revision required by this paragraph terminates the
actions required by paragraphs (f), (g), and (h) of AD 2004-07-22
R1. After accomplishing the revision required by this paragraph, the
revisions required by paragraphs (f), (g), and (h) of AD 2004-07-22
R1, as applicable, must be removed.
(1) For all airplanes except Model 747-400 LCF airplanes: SSIs
listed in Boeing Document No. D6-35022, ``Supplemental Structural
Inspection Document for Model 747 Airplanes,'' Revision H, dated
September 2013.
(2) For Model 747-400 LCF airplanes: SSIs listed in Boeing
Document No. D6-35022, ``Supplemental Structural Inspection Document
for Model 747 Airplanes,'' Revision H, dated September 2013; and
SSIs listed in Boeing Document No. D6-35022-1, ``747-400 LCF
Supplemental Structural Inspection Document--Appendix A,'' dated
November 2015. For SSIs listed in both Boeing Document No. D6-35022-
1, ``747-400 LCF Supplemental Structural Inspection Document--
Appendix A,'' dated November 2015; and Boeing Document No. D6-35022,
``Supplemental Structural Inspection Document for Model 747
Airplanes,'' Revision H, dated September 2013: Incorporate the SSIs
listed Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental
Structural Inspection Document--Appendix A,'' dated November 2015.
(i) Inspection Compliance Times for All Model 747 Airplanes Except
Model 747-400 LCF airplanes
For all Model 747 airplanes except Model 747-400 LCF airplanes:
Perform inspections to detect cracks of all structure identified in
Boeing Document No. D6-35022, ``Supplemental Structural Inspection
Document for Model 747 Airplanes,'' Revision H, dated September
2013, at the times specified in paragraph (i)(1), (i)(2), or (i)(3)
of this AD, as applicable. Once the initial inspection has been
performed, in order to remain in compliance with the maintenance or
inspection program, as required by paragraph (h) of this AD,
repetitive inspections are required at the intervals specified in
Boeing Document No. D6-35022, ``Supplemental Structural Inspection
Document for Model 747 Airplanes,'' Revision H, dated September
2013. Doing an inspection required by this paragraph terminates the
corresponding inspection required by paragraph (i) of AD 2004-07-22
R1.
(1) For wing structure, except as provided by paragraph (i)(3)
of this AD: Inspect at the times specified in paragraph (i)(1)(i) or
(i)(1)(ii) of this AD, whichever occurs later.
(i) Within the applicable compliance time specified in paragraph
(i)(1)(i)(A) or (i)(1)(i)(B) of this AD.
[[Page 62034]]
(A) For all Model 747-100, 747-100B, 747-100B SUD, 747-200B,
747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes:
Prior to the accumulation of 20,000 total flight cycles or 100,000
total flight hours, whichever occurs first.
(B) For all Model 747-400, 747-400D, and 747-400F series
airplanes: Prior to the accumulation of 20,000 total flight cycles
or 115,000 total flight hours, whichever occurs first.
(ii) Within 1,000 flight cycles or 12 months after the effective
date of this AD, whichever occurs later.
(2) For all structure other than wing structure, except as
provided by paragraph (i)(3) of this AD: At the time specified in
paragraph (i)(2)(i) or (i)(2)(ii) of this AD, whichever occurs
later.
(i) Prior to the accumulation of 20,000 total flight cycles.
(ii) Within 1,000 flight cycles or 12 months after the effective
date of this AD, whichever occurs later.
(3) For any portion of an SSI that has been replaced with new
structure: Inspect at the later of the times specified in paragraphs
(i)(3)(i) and (i)(3)(ii) of this AD.
(i) At the time specified in paragraph (i)(1) or (i)(2) of this
AD, as applicable.
(ii) Within 10,000 flight cycles after the replacement of the
part with a new part.
(j) Inspection Compliance Times for Model 747-400 LCF Airplanes
For Model 747-400 LCF airplanes: Perform inspections to detect
cracks of all structure identified in Boeing Document No. D6-35022,
``Supplemental Structural Inspection Document for Model 747
Airplanes,'' Revision H, dated September 2013; and Boeing Document
No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection
Document--Appendix A,'' dated November 2015; at the times specified
in paragraph (j)(1) or (j)(2) of this AD, as applicable. Once the
initial inspection has been performed, in order to remain in
compliance with the maintenance or inspection program, as required
by paragraph (h) of this AD, repetitive inspections are required at
the intervals specified in Boeing Document No. D6-35022,
``Supplemental Structural Inspection Document for Model 747
Airplanes,'' Revision H, dated September 2013; and Boeing Document
No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection
Document--Appendix A,'' dated November 2015. Where SSIs are listed
in both Boeing Document No. D6-35022, ``Supplemental Structural
Inspection Document for Model 747 Airplanes,'' Revision H, dated
September 2013; and Boeing Document No. D6-35022-1, ``747-400 LCF
Supplemental Structural Inspection Document--Appendix A,'' dated
November 2015; the SSIs listed in Boeing Document No. D6-35022-1,
``747-400 LCF Supplemental Structural Inspection Document--Appendix
A,'' dated November 2015, take precedence. Doing an inspection
required by this paragraph terminates the corresponding inspection
required by paragraph (i) of AD 2004-07-22 R1.
(1) For wing structure: Inspect at the times specified in
paragraph (j)(1)(i) or (j)(1)(ii) of this AD, whichever occurs
later.
(i) Prior to the accumulation of 20,000 total flight cycles or
115,000 total flight hours, whichever occurs first.
(ii) Within 1,000 flight cycles or 12 months after the effective
date of this AD, whichever occurs later.
(2) For all structure other than wing structure: At the time
specified in paragraph (j)(2)(i) or (i)(2)(ii) of this AD, whichever
occurs later.
(i) At the earlier of the times specified in paragraphs
(j)(2)(i)(A) and (j)(2)(i)(B) of this AD.
(A) Prior to the accumulation of 20,000 total flight cycles.
(B) Within the applicable initial compliance time specified in
Boeing Document No. D6-35022, ``Supplemental Structural Inspection
Document for Model 747 Airplanes,'' Revision H, dated September
2013; and Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental
Structural Inspection Document--Appendix A,'' dated November 2015.
Where SSIs are listed in both Boeing Document No. D6-35022,
``Supplemental Structural Inspection Document for Model 747
Airplanes,'' Revision H, dated September 2013; and Boeing Document
No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection
Document--Appendix A,'' dated November 2015; the SSIs listed in
Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental
Structural Inspection Document--Appendix A,'' dated November 2015,
take precedence.
(ii) Within 1,000 flight cycles or 12 months after the effective
date of this AD, whichever occurs later.
(k) Repair
If any cracked structure is found during any inspection required
by paragraph (i) or (j) of this AD, repair before further flight
using a method approved in accordance with the procedures specified
in paragraph (m) of this AD.
(l) Inspection Program for Transferred Airplanes
Before any airplane that is subject to this AD and that has
exceeded the applicable compliance times specified in paragraph (i)
or (j) of this AD can be added to an air carrier's operations
specifications, a program for the accomplishment of the inspections
required by this AD must be established in accordance with paragraph
(l)(1) or (l)(2) of this AD, as applicable.
(1) For airplanes that have been inspected as specified in this
AD, the inspection of each SSI must be accomplished by the new
operator using the previous operator's schedule and inspection
method, or the new operator's schedule and inspection method, at
whichever time would result in the earlier accomplishment for that
SSI inspection. The compliance time for accomplishment of this
inspection must be measured from the last inspection accomplished by
the previous operator. After each inspection has been performed
once, each subsequent inspection must be performed using the new
operator's schedule and inspection method.
(2) For airplanes that have not been inspected as specified in
this AD, the inspection of each SSI required by this AD must be
accomplished either prior to adding the airplane to the air
carrier's operations specification, or using a schedule and an
inspection method approved by the Manager, Seattle Aircraft
Certification Office (ACO). After each inspection has been performed
once, each subsequent inspection must be performed using the new
operator's schedule and inspection method.
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle 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
(n)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-
AMOC-Requests@faa.
(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.
(4) AMOCs approved for AD 2004-07-22 R1 are approved as AMOCs
for the corresponding provisions of paragraphs (h), (i), and (j) of
this AD for the SSIs identified in the AMOC, except for any SSI that
has an expanded inspection area identified in Boeing Document No.
D6-35022, ``Supplemental Structural Inspection Document for Model
747 Airplanes,'' Revision H, dated September 2013; or Boeing
Document No. D6-35022-1, ``747-400 LCF Supplemental Structural
Inspection Document--Appendix A,'' dated November 2015.
(n) Related Information
(1) For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428;
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 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.
[[Page 62035]]
Issued in Renton, Washington, on August 24, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-21147 Filed 9-7-16; 8:45 am]
BILLING CODE 4910-13-P