[Federal Register Volume 82, Number 192 (Thursday, October 5, 2017)]
[Rules and Regulations]
[Pages 46382-46385]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-19041]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9183; Product Identifier 2016-NM-059-AD; Amendment 
39-19029; AD 2017-18-20]
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 The 
Boeing Company Model 707 airplanes equipped with a main cargo door 
(MCD). This AD was prompted by analysis of the cam support assemblies 
of the MCD that indicated the repetitive high frequency eddy current 
(HFEC) inspections required by the existing maintenance program are not 
adequate to detect cracks before two adjacent cam support assemblies of 
the MCD could fail. This AD requires repetitive ultrasonic inspections 
for cracking of the cam support assemblies of the MCD, and replacement 
if necessary. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective November 9, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 9, 
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 service information at the 
FAA, Transport Standards Branch, 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-
9183.

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-
9183; 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 final rule, 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: Chandra Ramdoss, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-
5210; email: <a href="/cdn-cgi/l/email-protection#57343f36393325363322233f7925363a333824241731363679303821"><span class="__cf_email__" data-cfemail="a3c0cbc2cdc7d1c2c7d6d7cb8dd1c2cec7ccd0d0e3c5c2c28dc4ccd5">[email protected]</span></a>.

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 all The Boeing Company 
Model 707 airplanes. The NPRM published in the Federal Register on 
October 4, 2016 (81 FR 68376) (``the NPRM''). The NPRM was prompted by 
analysis of the cam support assemblies of the MCD that indicated the 
repetitive HFEC inspections required by the existing maintenance 
program are not adequate to detect cracks before two adjacent cam 
support assemblies of the MCD could fail. The NPRM proposed to require 
repetitive ultrasonic inspections for cracking of the cam support 
assemblies of the MCD, and replacement if necessary. We are issuing 
this AD to detect and correct cracking of the cam support assemblies of 
the MCD. Such cracking could result in reduced structural integrity of 
the MCD and consequent rapid decompression of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment.
Request To Revise Applicability
    Boeing stated that Boeing 707 Alert Service Bulletin A3542, dated 
February 12, 2016, affects only Boeing factory and Boeing-converted 
freighters, but the proposed AD extends the applicability to all Model 
707 airplanes, including the ones that have been converted by non-
Boeing supplemental type certificates (STCs).
    We infer the commenter is requesting that the actions of the 
service information only be required for Model 707 airplanes identified 
in the Effectivity paragraph of Boeing 707 Alert Service Bulletin 
A3542, dated February 12, 2016. We agree that the applicability of the 
proposed AD should not include Model 707 airplanes that do not have an 
MCD. However, we disagree that the AD applicability should be limited 
to the airplanes identified in the Effectivity paragraph of Boeing 707 
Alert Service Bulletin A3542, dated February 12, 2016, which only 
identifies Boeing factory and Boeing-converted freighters. The cam 
support assemblies having the affected part number could be installed 
at original aircraft manufacture, or during passenger-to-freighter 
modification. We expect that the actions specified in Boeing 707 Alert 
Service Bulletin A3542, dated February 12, 2016, can be accomplished on 
airplanes that are not identified in that service information. However, 
if an operator with a Model 707 freighter that is not a part of Boeing 
type design cannot accomplish the required actions in the service 
information, or prefers to use different service information that is 
specific to their design, approval of an alternative method of 
compliance (AMOC) can be requested in accordance with paragraph (j) of 
this AD. We revised this AD to limit the applicability to Model 707 
airplanes equipped with an MCD.
Request To Supersede AD 80-08-10 R1, Amendment 39-3830 (45 FR 46343, 
July 10, 1980) (``AD 80-08-10 R1'')
    Boeing requested that we revise the NPRM to supersede AD 80-08-10 
R1. Boeing stated that AD 80-08-10 R1 mandates HFEC inspections of MCD 
cam support assemblies having part numbers (P/Ns) 69-23588-1 and 69-
23588-2, as specified in Boeing Service Bulletin 707-A3387. Boeing 
explained that the NPRM is adding cam support assemblies having P/Ns 
69-23588-1 and 69-23588-2 to the list in Boeing 707 Alert Service 
Bulletin A3542, dated February 12, 2016. Boeing asserted that the 
addition of these components to the list of affected parts would mean 
that the operators have to perform HFEC inspections of cam support 
assemblies having P/Ns 69-23588-1 and 69-23588-2, as specified in AD 
80-08-10 R1, and perform ultrasonic inspections of the same components, 
as specified in the proposed AD. Boeing explained that

[[Page 46383]]

cracking initiates at the bottom of the lubrication hole on the inside 
of the cam support fitting lug and is not visible until it breaks to 
the surface of the lug. The subsurface detection capability of the 
ultrasonic inspection provides a more reliable inspection.
    We partially agree with Boeing's request to supersede the 
inspections which are still required per AD 80-08-10 Rl. These 
inspections will overlap with the newly mandated repetitive 
inspections. We disagree with the request to revise this AD to 
supersede AD 80-08-10 Rl. Instead, we have added language to paragraph 
(i) of this AD to state that accomplishing the initial inspection and 
all applicable replacements required by paragraph (h) of this AD on an 
airplane terminates the requirements of AD 80-08-10 R1, for that 
airplane only.
Request To Revise Compliance Time
    Boeing requested that we revise the compliance time in paragraph 
(g)(l) of the proposed AD from ``before the accumulation of 18,000 
total flight cycles'' to ``before the accumulation of 18,000 door 
flight cycles, or within 10 years after the utilization of MCD cam 
support assemblies, whichever occurs first. If the door flight cycles 
are not known, use total airplane flight cycles.'' Boeing explained 
that this change would provide relief for the operators that use 
converted freighters by delaying the required inspection for the MCDs 
that have been in service less than 18,000 total door flight cycles, 
but are installed on the airplanes that have more than 18,000 total 
airframe flight cycles. Boeing also stated that the 10-year time limit 
is included in Boeing 707 Alert Service Bulletin A3542, dated February 
12, 2016, to address the low utilization rate of Model 707/720 
airplanes.
    We agree with Boeing's request. For the airplanes that have been 
converted to freighters, the compliance time for the initial inspection 
should be based on the number of cycles the MCD cam support assembly 
has been in service. We have revised paragraph (g)(l) of this AD 
accordingly. In addition, we have revised paragraph (h) of this AD to 
refer to the compliance times specified in paragraphs (g)(1) and (g)(2) 
of this AD instead of referring to Boeing 707 Alert Service Bulletin 
A3542, dated February 12, 2016. We have also removed the exception to 
the service information that was in paragraph (i) of the proposed AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the changes described previously and minor 
editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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 final 
rule.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing 707 Alert Service Bulletin A3542, dated February 
12, 2016. The service information describes procedures for an 
ultrasonic inspection of the cam support assemblies of the MCD for 
cracking, and replacement if necessary. 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 will affect 12 airplanes of U.S. registry. 
We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  6 work-hours x $85               $0   $510 per inspection  $22,950 per
                                   per hour = $510                       cycle.               inspection cycle.
                                   per inspection
                                   cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need this 
replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement..................................  60 work-hours x $85 per hour =          $14,107          $19,207
                                                $5,100.
----------------------------------------------------------------------------------------------------------------

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a

[[Page 46384]]

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):

2017-18-20 The Boeing Company: Amendment 39-19029; Docket No. FAA-
2016-9183; Product Identifier 2016-NM-059-AD.

(a) Effective Date

    This AD is effective November 9, 2017.

(b) Affected ADs

    This AD affects AD 80-08-10 R1, Amendment 39-3830 (45 FR 46343, 
July 10, 1980).

(c) Applicability

    This AD applies to The Boeing Company Model 707-100 Long Body, -
200, -100B Long Body, and -100B Short Body series airplanes; and 
Model 707-300, -300B, -300C, and -400 series airplanes; certificated 
in any category; equipped with a main cargo door (MCD).

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Unsafe Condition

    This AD was prompted by analysis of the cam support assemblies 
of the MCD that indicated the repetitive high frequency eddy current 
(HFEC) inspections required by the existing maintenance program are 
not adequate to detect cracks before two adjacent cam support 
assemblies of the MCD could fail. We are issuing this AD to detect 
and correct cracking of the cam support assemblies of the MCD. Such 
cracking could result in reduced structural integrity of the MCD and 
consequent rapid decompression of the airplane.

(f) Compliance

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

(g) Inspection to Determine Part Numbers

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Inspect the cam support assemblies of the MCD to 
determine whether part number (P/N) 69-23588-1, 69-23588-2, 69-
23588-5, 69-23588-6, 69-23588-9, or 69-23588-10 is installed. A 
review of airplane maintenance records is acceptable in lieu of this 
inspection if the part number(s) of the cam support assemblies of 
the MCD can be conclusively determined from that review.
    (1) Before the accumulation of 18,000 total flight cycles since 
installation of the door, or before the accumulation of 10 years on 
the MCD cam support assemblies, whichever occurs first. If the 
number of flight cycles since installation of the door are not 
known, use total airplane flight cycles.
    (2) Within 1,790 flight cycles or 24 months after the effective 
date of this AD, whichever occurs later.

(h) Repetitive Inspections of the Cam Support Assemblies of the MCD and 
Corrective Actions

    If, during any inspection required by paragraph (g) of this AD, 
any cam support assembly of the MCD having P/N 69-23588-1, 69-23588-
2, 69-23588-5, 69-23588-6, 69-23588-9, or 69-23588-10 is determined 
to be installed: At the later of the times specified in paragraphs 
(g)(1) and (g)(2) of this AD, do an ultrasonic inspection to detect 
cracking of the affected cam support assemblies of the MCD, and do 
all applicable replacements, in accordance with the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3542, dated 
February 12, 2016. Do all applicable replacements before further 
flight. Repeat the inspections thereafter at the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Boeing 707 Alert 
Service Bulletin A3542, dated February 12, 2016.

(i) Terminating Action for AD 80-08-10 R1, Amendment 39-3830 (45 FR 
46343, July 10, 1980)

    Accomplishment of the initial inspection and all applicable 
replacements on an airplane, as required by paragraph (h) of this 
AD, terminates all the requirements of AD 80-08-10 R1, Amendment 39-
3830 (45 FR 46343, July 10, 1980), for that airplane only.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of 
the person identified in paragraph (k) of this AD. Information may 
be emailed to: <a href="/cdn-cgi/l/email-protection#a89185e9e6e585e4e9e9ebe785e9e5e7eb85facdd9ddcddbdcdbe8cec9c986cfc7de"><span class="__cf_email__" data-cfemail="566f7b17181b7b1a171715197b171b19157b04332723332522251630373778313920">[email protected]</span></a>.
    (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, Los Angeles ACO Branch, 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 
(j)(4)(i) and (j)(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.

(k) Related Information

    For more information about this AD, contact Chandra Ramdoss, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5239; fax: 562-627-5210; email: <a href="/cdn-cgi/l/email-protection#89eae1e8e7edfbe8edfcfde1a7fbe8e4ede6fafac9efe8e8a7eee6ff"><span class="__cf_email__" data-cfemail="7b18131a151f091a1f0e0f1355091a161f1408083b1d1a1a551c140d">[email protected]</span></a>.

(l) 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 707 Alert Service Bulletin A3542, dated February 12, 
2016.
    (ii) Reserved.
    (3) For 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;

[[Page 46385]]

telephone 562-797-1717; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 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 August 31, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-19041 Filed 10-4-17; 8:45 am]
 BILLING CODE 4910-13-P


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