[Federal Register Volume 82, Number 109 (Thursday, June 8, 2017)]
[Proposed Rules]
[Pages 26617-26619]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-11893]



[[Page 26617]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0251; Directorate Identifier 2016-NM-101-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking.

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for The 
Boeing Company Model 757-200 series airplanes with certain supplemental 
type certificates. This proposed AD was prompted by a report indicating 
that the main cargo door (MCD) forward-most cam latch on the forward 
center cam latch pair broke during flight. This proposed AD would 
require repetitive inspections for discrepancies of cam latches, latch 
pins, and latch pin cross bolts of the MCD; replacement of all alloy 
steel cross bolts through the latch pins with corrosion-resistant steel 
(CRES) cross bolts of the MCD; and related investigative and corrective 
actions if necessary. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by July 24, 2017.

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 VT Mobile 
Aerospace Engineering Inc., 2100 9th Street, Brookley Aeroplex, Mobile, 
AL 36615; telephone: 251-379-0112; email: [email protected]; 
Internet: http://www.vtmae.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-2017-
0251; 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 (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Samuel Belete, Aerospace Engineer, 
Systems and Equipment Branch, ACE-119A, FAA, Atlanta Aircraft 
Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 
30337; telephone: 404-474-5580; fax: 404-474-5605; 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-2017-0251; 
Directorate Identifier 2016-NM-101-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

    We have received a report indicating that a forward-most cam latch 
of the forward center cam latch pair on a Model 757 airplane MCD broke 
during flight. We issued AD 2015-25-01, Amendment 39-18339 (80 FR 
79461, December 22, 2015) (``AD 2015-25-01''), to address the unsafe 
condition for The Boeing Company Model 757-200, 757-200CB, and 767-
200PF series airplanes delivered under a Boeing supplemental type 
certificate. We have determined that action is needed to address the 
same unsafe condition on Model 757-200 series airplanes that have been 
converted from a passenger to a freighter configuration in accordance 
with VT Mobile Aerospace Engineering Inc. (MAE) Supplemental Type 
Certificate (STC) ST03562AT (14 pallet) or VT MAE STC ST04242AT (15 
pallet), and from passenger to combination cargo/passenger 
configuration in accordance with VT MAE STC ST03952AT (combi). The VT 
MAE MCD cam latches and latch pins are similar to those in the Boeing 
MCD addressed in AD 2015-25-01. However, AD 2015-25-01 does not include 
the airplanes addressed in this proposed AD. We are proposing this AD 
to detect and correct discrepancies of the MCD cam latches, latch pins, 
and latch pin cross bolts, which, if left undetected, could reduce the 
structural integrity of the MCD, and result in potential loss of the 
cargo door and rapid decompression of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed VT Mobile Aerospace Engineering Inc. Service Bulletin 
MAE757SF-SB-52-12/02, Revision 3, dated July 22, 2016 (``MAE757SF-SB-
52-12/02, R3''). The service information describes procedures for doing 
inspections for discrepancies of cam latches, latch pins, and latch pin 
cross bolts of the MCD; replacement of all alloy steel cross bolts 
through the latch pins with CRES cross bolts of the MCD; and related 
investigative and corrective actions. 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 accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.''
    Related investigative actions include detailed inspections of 
mating parts and adjacent cam latches and cam pins for cracks and 
gouges, high frequency eddy current or magnetic particle inspection of 
cam latches for cracks, and checks of the rig of the MCD. Corrective 
actions include replacing discrepant parts, repairing damage, and 
rigging the MCD.

[[Page 26618]]

    The compliance time for the general visual inspection is 375 flight 
cycles after the rig of the MCD was checked. The initial compliance 
time for the other inspections is before the accumulation of 40,000 
total latch pin flight cycles, or 3,000 or 6,000 flight cycles after 
the rig of the MCD was checked. The compliance time for the replacement 
is 3,000 flight cycles after the rig of the MCD was checked. The 
compliance times for the repetitive inspections range from 375 flight 
cycles to 6,000 flight cycles.

Differences Between This Proposed AD and the Service Information

    Where MAE757SF-SB-52-12/02, R3, specifies doing actions on 
airplanes meeting certain conditions identified in the ``Condition'' 
column of table 1 of paragraph I.D., ``Compliance,'' this proposed AD 
specifies doing these actions on all airplanes.

Costs of Compliance

    We estimate that this proposed AD affects 119 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
            Action                     Labor cost           Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections...................  20 work-hours x $85 per               $0  $1,700 per          $202,300 per
                                 hour = $1,700 per                         inspection cycle.   inspection cycle.
                                 inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary related 
investigative and corrective actions that would be required based on 
the results of the proposed inspection. We have no way of determining 
the number of aircraft that might need these actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                      Labor cost              Parts cost             Cost per product
----------------------------------------------------------------------------------------------------------------
Related investigative and          Up to 144 work-hours x    Up to $3,000.......  Up to $15,240.
 corrective actions.                $85 per hour = $12,240.
----------------------------------------------------------------------------------------------------------------

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),
    (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-2017-0251; Directorate Identifier 
2016-NM-101-AD.

(a) Comments Due Date

    We must receive comments by July 24, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 757-200 series 
airplanes, certificated in any category, that have been converted 
from passenger to freighter configuration as specified in any of the 
VT Mobile Aerospace Engineering Inc. Supplemental Type Certificates 
(STCs) identified in paragraphs (c)(1), (c)(2), and (c)(3) of this 
AD.
    (1) ST03562AT (14 pallet) (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
7239683609eb1b4086257ff1004d0f2b/$FILE/ST03562AT.pdf).
    (2) ST04242AT (15 pallet) (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
edd46d607cedd3a286257ff1004d8d82/$FILE/ST03952AT.pdf.)
    (3) ST03952AT (combi--airplanes that can carry passenger, 
freight, or both in the cabin) (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
edd46d607cedd3a286257ff1004d8d82/$FILE/ST03952AT.pdf).

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report indicating that the main cargo 
door (MCD) forward-most cam latch on the forward center cam latch 
pair broke during flight. We are issuing this AD to detect and 
correct

[[Page 26619]]

discrepancies of the MCD cam latches, latch pins, and latch pin 
cross bolts, which, if left undetected, could reduce the structural 
integrity of the MCD and result in potential loss of the cargo door 
and rapid decompression of the airplane.

(f) Compliance

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

(g) Repetitive Inspections, Replacement, and Related Investigative and 
Corrective Actions

    At the applicable time specified in paragraph I.D., 
``Compliance,'' of VT Mobile Aerospace Engineering Inc. Service 
Bulletin MAE757SF-SB-52-12/02, Revision 3, dated July 22, 2016 
(``MAE757SF-SB-52-12/02, R3''), except as required by paragraph 
(h)(1) of this AD; or within 30 days after the effective date of 
this AD, whichever occurs later: Do the actions specified in 
paragraphs (g)(1) through (g)(4) of this AD, and do all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of MAE757SF-SB-52-12/02, R3, except as 
specified in paragraph (h)(2) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspections specified in paragraphs (g)(1), (g)(2), and (g)(4) 
of this AD thereafter at the applicable intervals specified in 
paragraph I.D., ``Compliance,'' of MAE757SF-SB-52-12/02, R3.
    (1) Do a general visual inspection for any broken or missing cam 
latches, latch pins, and latch pin cross bolts of the MCD.
    (2) Do a detailed inspection for any cracks or gouges in 
critical areas of the cam latches and latch pins of the MCD and for 
any cam latches with lip deformation.
    (3) Replace all previously unreplaced alloy steel cross bolts 
through the latch pins with corrosion resistant steel (CRES) cross 
bolts of the MCD.
    (4) Do a high frequency eddy current (HFEC) or magnetic particle 
inspection for any cracks in the critical areas of cam latch 1 and 
cam latch 2 of the MCD.

(h) Exceptions to Service Information

    (1) Where the ``Condition'' column of table 1 of paragraph I.D., 
``Compliance,'' of MAE757SF-SB-52-12/02, R3, refers to airplanes 
meeting certain conditions identified in ``Condition 1'': for this 
AD, ``Condition 1'' applies to all airplanes.
    (2) Where the Accomplishment Instructions of MAE757SF-SB-52-12/
02, R3, specify doing actions only for airplanes that had completed 
a certain rig and check of the MCD on them, this AD requires doing 
those actions on all airplanes.

(i) 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 VT Mobile Aerospace Engineering Inc. 
Service Bulletin MAE757SF-SB-52-12/02, Revision 2, dated February 
18, 2016.

(j) Special Flight Permit

    A special flight permit may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane, for a single 
unpressurized flight, to a location where the airplane can be 
modified.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta 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)(1) of this AD.
    (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.

(l) Related Information

    (1) For more information about this AD, contact Samuel Belete, 
Aerospace Engineer, Systems and Equipment Branch, ACE-119A, FAA, 
Atlanta ACO, 1701 Columbia Avenue, College Park, GA 30337; telephone 
404-474-5580; fax 404-474-5605; email: [email protected].
    (2) For service information identified in this AD, contact VT 
Mobile Aerospace Engineering Inc., 2100 9th Street, Brookley 
Aeroplex, Mobile, AL 36615; telephone: 251-379-0112; email: 
[email protected]; Internet: http://www.vtmae.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.

    Issued in Renton, Washington, on April 11, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-11893 Filed 6-7-17; 8:45 am]
 BILLING CODE 4910-13-P