[Federal Register Volume 81, Number 217 (Wednesday, November 9, 2016)]
[Rules and Regulations]
[Pages 78711-78714]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-26163]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0462; Directorate Identifier 2015-NM-144-AD; 
Amendment 39-18703; AD 2016-22-14]
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 737-600, -700, -700C, -800, -900, and -900ER 
series airplanes. This AD was prompted by a report of wire chafing 
damage, which caused an electrical arc to an adjacent hydraulic tube 
located on the forward bulkhead of the main landing gear (MLG) wheel 
well, resulting in a hole in a hydraulic tube and consequent total loss 
of system B hydraulic fluid. This AD requires an inspection for chafing 
damage of wire bundles and a hydraulic tube in the right side of the 
MLG wheel well, and corrective action if necessary; and installation of 
clamps between the wire bundles and hydraulic tube. We are issuing this 
AD to prevent chafing damage, which could result in electrical arcing 
that can cause a hole in the hydraulic tube and consequent loss of 
hydraulic fluid, possibly resulting in a fire in the MLG wheel well.

DATES: This AD is effective December 14, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 14, 
2016.

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-
0462.

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-
0462; 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: Sean J. Schauer, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA. 98057-
3356; phone: 425-917-6479; fax: 425-917-6590; email: 
[email protected].

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 737-600, -700, -700C, -800, -900, and -900ER series airplanes. 
The NPRM published in the Federal Register on February 8, 2016 (81 FR 
6475) (``the NPRM''). The NPRM was prompted by a report of wire chafing 
damage, which caused an electrical arc to an adjacent hydraulic tube 
located on the forward bulkhead of the MLG wheel well, resulting in a 
hole in a hydraulic tube and consequent total loss of system B 
hydraulic fluid. The NPRM proposed to require an inspection for chafing 
damage of wire bundles and a hydraulic tube in the right side of the 
MLG wheel well, and corrective action if necessary; and installation of 
clamps between the wire bundles and hydraulic tube. We are issuing this 
AD to prevent chafing damage, which could result in electrical arcing 
that can cause a hole in the hydraulic tube and consequent loss of 
hydraulic fluid, possibly resulting in a fire in the MLG wheel well.

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.

Support for the NPRM

    The Air Line Pilots Association, International and an anonymous 
commenter supported the NPRM.

Request for Clarification

    The European Aviation Safety Agency (EASA) requested that we 
respond to the following questions.
     EASA stated that the NPRM looks very similar to AD 2013-
19-03, Amendment 39-17585 (78 FR 59798, September 30, 2013) (``AD 2013-
19-03''). EASA asked if there is a more fundamental problem with wiring 
harnesses in the landing gear bay in the Model 737 fleet.
    We agree that the unsafe conditions identified in this AD and in AD 
2013-19-03 are similar; however, the reasons for the unsafe conditions, 
and the associated corrective actions in these ADs, differ. This 
difference is due to the occurrence of wire chafing in different 
locations in the landing gear bay. The underlying issue is limited 
space for the electrical system routing in the landing gear bay.
     EASA asked whether there is sufficient accessibility to 
inspect the affected area.
    We have determined that there is sufficient space to inspect the 
landing gear bay.
     EASA asked why the spacer is only an optional action.
    The source of service information that we reference in this AD, 
Boeing Alert Service Bulletin 737-29A1119, Revision 1, dated June 23, 
2016 (``ASB 737-29A1119 R1''), specifies that the spacer addition is 
optional for cases where additional spacing is needed to allow adequate 
clearance.
     EASA asked what measures have been put in place to ensure 
the safety of

[[Page 78712]]

the fleet, pending the proposed inspection.
    We consider that the standard operational procedures that are in 
place regarding loss of system B hydraulic pressure or a wheel well 
fire to be adequate to ensure the safety of the fleet, pending the 
completion of the actions required in this AD.
     EASA asked if the wire chafing issue is one of design with 
regulations, or non-compliance of the product with the design data.
    We have determined that the issue is due to nonconformance to the 
design data.
    No changes to the final rule are necessary in regard to the 
questions asked by EASA.

Requests To Reference New Service Information

    All Nippon Airways (ANA), Boeing, Japan Airlines, Qantas Airways, 
Southwest Airlines, and United Airlines (UA) requested that we 
reference Boeing Service Bulletin Information Notice 737-29A1119 IN 01, 
dated August 25, 2015; and Boeing Service Bulletin Information Notice 
737-29A1119 IN 02, dated November 02, 2015; and new service information 
ASB 737-29A1119 R1. ANA commented that Boeing will not ship the top 
kits of needed parts until the release of ASB 737-29A1119 R1. UA 
requested that ASB 737-29A1119 R1 incorporate the Required for 
Compliance (RC) format.
    We agree with the commenters' requests to incorporate ASB 737-
29A1119 R1 as an appropriate source of service information. This 
service information incorporates the revisions in the Boeing 
information notices referenced by the commenters. In ASB 737-29A1119 
R1, the part number of the subject wiring harness clamp has been 
corrected, the work instructions have been rewritten to improve 
operator usability, and the RC steps have been added. We have revised 
paragraphs (c), (g)(1), and (g)(2) of this AD to specify ASB 737-
29A1119 R1. We have added a new paragraph (h) to this AD to give credit 
for actions done prior to the effective date of this AD using Boeing 
Alert Service Bulletin 737-29A1119, dated August 4, 2015, and 
redesignated subsequent paragraphs accordingly. We have also added new 
paragraph (i)(4) to this AD to address the RC language specified in ASB 
737-29A1119 R1.

Request To Revise Paragraph (g) of the Proposed AD

    One commenter, Evki Meto, requested that we revise paragraph (g)(1) 
of the proposed AD, which proposed inspecting for chafing damage. The 
commenter requested that we expand the inspection to look for any 
damage. No reason was provided by the commenter.
    We disagree with the commenter's request. We have determined that 
the inspection in paragraph (g) of this AD should emphasize chafing 
damage, as that damage relates to the unsafe condition being addressed 
by this AD. We have not changed this AD in this regard.

Request To Revise Compliance Time

    KLM Royal Dutch Airlines (KLM) requested that we revise the 24-
month compliance time to 30 months. KLM stated that it intends to do 
the modification during C-check maintenance, but will not be able to 
comply without impact to its maintenance program with the 24-month 
compliance time due to its C-check maintenance interval, which is 30 
months.
    We do not agree with the commenter's request. In developing an 
appropriate compliance time, we considered the safety implications, 
parts availability, and normal maintenance schedules for timely 
accomplishment of the required actions. Further, we arrived at the 
compliance time with manufacturer concurrence. In consideration of all 
of these factors, we determined that the compliance time of 24 months 
represents an appropriate interval in which the inspections can be done 
in a timely manner within the fleet, while still maintaining an 
adequate level of safety. Under the provisions of paragraph (i) of this 
AD, however, we will consider requests for approval of an alternative 
compliance time if sufficient data are submitted to substantiate that 
an alternate compliance time would provide an acceptable level of 
safety. We have not changed this AD in this regard.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that the installation of winglets 
per Supplemental Type Certificate (STC) ST00830SE does not affect the 
accomplishment of the manufacturer's service instructions.
    We agree with the commenter that STC ST00830SE does not affect the 
accomplishment of the manufacturer's service instructions. Therefore, 
the installation of STC ST00830SE does not affect the ability to 
accomplish the actions required by this AD. We have not changed this AD 
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:
     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.
    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 ASB 737-29A1119 R1. The service information describes 
procedures for doing an inspection for chafing damage of the wire 
bundles and hydraulic tube in the right side of the MLG wheel well, 
corrective actions, and installation of clamps and an optional spacer 
between the wire bundles and hydraulic tube. 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 1,270 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
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                                                                                    Cost per       Cost on U.S.
             Action                       Labor cost              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection and Installation....  2 work-hours x $85 per hour               $9             $179         $227,330
                                  = $170.
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[[Page 78713]]

    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):

2016-22-14 The Boeing Company: Amendment 39-18703; Docket No. FAA-
2016-0462; Directorate Identifier 2015-NM-144-AD.

(a) Effective Date

    This AD is effective December 14, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-600, 737-700, 
737-700C, 737-800, 737-900, and 737-900ER series airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin 737-29A1119, Revision 1, dated June 23, 2016 (``ASB 737-
29A1119 R1'').

(d) Subject

    Air Transport Association (ATA) of America Code 29, Hydraulic 
power.

(e) Unsafe Condition

    This AD was prompted by a report of wire chafing damage, which 
caused an electrical arc to an adjacent hydraulic tube located on 
the forward bulkhead of the main landing gear (MLG) wheel well, 
resulting in a hole in a hydraulic tube and consequent total loss of 
system B hydraulic fluid. We are issuing this AD to prevent chafing 
damage, which could result in electrical arcing that can cause a 
hole in the hydraulic tube and consequent loss of hydraulic fluid, 
possibly resulting in a fire in the MLG wheel well.

(f) Compliance

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

(g) Inspection and Corrective Action and Clamp Installation

    Within 24 months after the effective date of this AD: Do the 
actions specified in paragraphs (g)(1) and (g)(2) of this AD.
    (1) Do a detailed inspection for chafing damage of the wire 
bundles and hydraulic tube in the right side of the MLG wheel well, 
and do all applicable corrective actions, in accordance with the 
Accomplishment Instructions of ASB 737-29A1119 R1. Do all applicable 
corrective actions before further flight.
    (2) Install new clamps and an optional spacer between the wire 
bundles and hydraulic tube in the right side of the MLG wheel well, 
in accordance with the Accomplishment Instructions of ASB 737-
29A1119 R1.

(h) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Alert Service Bulletin 737-
29A1119, dated August 4, 2015. This service information is not 
incorporated by reference in this AD.

(i) 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 (j)(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, 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) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(i)(4)(i) and (i)(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 substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. 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.

(j) Related Information

    (1) For more information about this AD, contact Sean J. Schauer, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6479; fax: 425-917-6590; 
email: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k)(3) and (k)(4) of this AD.

[[Page 78714]]

(k) 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 737-29A1119, Revision 1, dated 
June 23, 2016.
    (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 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 October 25, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-26163 Filed 11-8-16; 8:45 am]
BILLING CODE 4910-13-P