
[Federal Register Volume 82, Number 7 (Wednesday, January 11, 2017)]
[Rules and Regulations]
[Pages 3137-3140]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-31187]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8181; Directorate Identifier 2016-NM-002-AD; 
Amendment 39-18765; AD 2016-26-07]
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, 
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 
747SP series airplanes. This AD was prompted by an evaluation by the 
design approval holder (DAH) indicating that the nose wheel well is 
subject to widespread fatigue damage (WFD). This AD requires 
modification, inspections, and corrective actions of the nose wheel 
body structure. We are issuing this AD to address the unsafe condition 
on these products.

DATES: This AD is effective February 15, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 15, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone: 562-797-1717; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8181.

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-
8181; 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

[[Page 3138]]

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 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: Nathan.P.Weigand@faa.gov.

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, 747-200C, 747-200F, 
747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series 
airplanes. The NPRM published in the Federal Register on July 28, 2016 
(81 FR 49572) (``the NPRM''). The NPRM was prompted by an evaluation by 
the DAH indicating that the nose wheel well is subject to WFD. The NPRM 
proposed to require modification of the nose wheel body structure; a 
detailed inspection of the nose wheel body structure for any cracking; 
a surface HFEC or an open hole HFEC inspection of the vertical beam 
outer chord and web for any cracking; and all applicable related 
investigative actions including repetitive inspections, and other 
specified and corrective actions. We are issuing this AD to detect and 
correct fatigue cracking in the nose wheel well structure; such 
cracking could adversely affect the structural integrity of the 
airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. Boeing and United 
Airlines supported the NPRM.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed, except for minor editorial changes. We have 
determined that these minor changes:
     Are 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.

Since the NPRM was Issued

    Since the NPRM was issued, we have updated the AD with Boeing's new 
contact information.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2887, dated 
December 2, 2015. The service information describes procedures for 
modification of the nose wheel body structure; a detailed inspection of 
the nose wheel body structure for any cracking; a web surface HFEC and 
an open hole HFEC inspection of the vertical beam outer chord for any 
cracking; 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 107 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
           Action                  Labor cost         Parts cost               Cost per product                        Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Modification................  408 work-hours x $85         $15,743  $50,423..............................  $5,395,261.
                               per hour = $34,680.
Part 2 detailed inspection..  140 work-hours x $85              $0  $11,900 per inspection cycle.........  $1,273,300 per inspection cycle.
                               per hour = $11,900
                               per inspection
                               cycle.
Surface HFEC inspection.....  4 work[dash]hours x               $0  $340 per inspection cycle............  Up to $36,380 per inspection cycle.
                               $85 per hour = $340
                               per inspection
                               cycle.
Open hole HFEC inspection...  4 work-hours x $85                $0  $340 per inspection cycle............  Up to $36,380 per inspection cycle.
                               per hour = $340 per
                               inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    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.

[[Page 3139]]

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):

2016-26-07 The Boeing Company: Amendment 39-18765; Docket No. FAA-
2016-8181; Directorate Identifier 2016-NM-002-AD.

(a) Effective Date

    This AD is effective February 15, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to 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, as identified in Boeing Alert Service Bulletin 747-
53A2887, dated December 2, 2015.

(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 indicating that the nose wheel well is subject to widespread 
fatigue damage. We are issuing this AD to detect and correct fatigue 
cracking in the nose wheel well structure; such cracking could 
adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) Modification for Groups 1 and 4 Airplanes

    For groups 1 and 4 airplanes as identified in Boeing Alert 
Service Bulletin 747-53A2887, dated December 2, 2015: Except as 
required by paragraph (j)(1) of this AD, at the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2887, dated December 2, 2015, modify the nose wheel 
body structure, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-53A2887, dated December 2, 
2015.

(h) Inspection for Groups 1 and 4 Airplanes

    For groups 1 and 4 airplanes on which the actions of paragraph 
(g) have been done: Except as required by paragraph (j)(1) of this 
AD, at the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2887, dated 
December 2, 2015, do a detailed inspection of the nose wheel body 
structure for any cracking; do a surface high frequency eddy current 
inspection (HFEC) or an open hole HFEC inspection of the vertical 
beam outer chord and web for any cracking; and do all applicable 
related investigative, other specified actions, and corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2887, dated December 2, 2015; 
except as required by paragraph (j)(2) of this AD. Do all applicable 
related investigative actions, other specified actions, and 
corrective actions before further flight. Repeat the detailed 
inspection of the nose wheel body structure, and either the surface 
HFEC or the open hole HFEC inspection of the vertical beam outer 
chord, thereafter, at the applicable interval specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2887, 
dated December 2, 2015.

(i) Inspection for Groups 2, 3, 5 and 6 Airplanes

    For groups 2, 3, 5 and 6 airplanes identified in Boeing Alert 
Service Bulletin 747-53A2887, dated December 2, 2015: Except as 
required by paragraph (j)(1) of this AD, at the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2887, dated December 2, 2015, do a detailed 
inspection of the nose wheel well body structure for any cracking, 
and do all applicable related investigative and corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2887, dated December 2, 2015; except as 
required by paragraph (j)(2) of this AD. Do all related 
investigative and corrective actions before further flight. Repeat 
the detailed inspection thereafter at the applicable intervals 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2887, dated December 2, 2015.

(j) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 747-53A2887, dated 
December 2, 2015, specifies a compliance time ``after the original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.
    (2) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 747-53A2887, dated December 2, 
2015, specifies to contact Boeing for appropriate action, and 
specifies that action as ``RC'' (Required for Compliance): Before 
further flight, repair using a method approved in accordance with 
the procedures specified in paragraph (k) of this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (l) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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) Except as required by paragraph (j)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and 
(k)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or sub-step is labeled ``RC Exempt,'' then 
the RC requirement is removed from that step or sub-step. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(l) Related Information

    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: Nathan.P.Weigand@faa.gov.

(m) 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 747-53A2887, dated December 2, 
2015.

[[Page 3140]]

    (ii) Reserved.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Contractual & Data 
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 
90740-5600; telephone: 562-797-1717; Internet: https://www.myboeingfleet.com.
    (4) You may view this 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.
    (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 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 15, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-31187 Filed 1-10-17; 8:45 am]
 BILLING CODE 4910-13-P


