[Federal Register Volume 83, Number 27 (Thursday, February 8, 2018)]
[Proposed Rules]
[Pages 5576-5579]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02085]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0031; Product Identifier 2017-NM-127-AD]
RIN 2120-AA6417


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 727 airplanes. This proposed AD was 
prompted by significant changes made to the airworthiness limitations 
(AWLs) related to fuel tank ignition prevention. This proposed AD would 
require revising the maintenance or inspection program, as applicable, 
to incorporate the latest revision of the AWLs. We are proposing this 
AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by March 26, 2018.

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: 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-2018-0031.

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-2018-
0031; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Christopher Baker, Aerospace Engineer, 
Propulsion Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW, 
Renton, WA 98057-3356; phone: 425-917-6498; 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-2018-0031; 
Product Identifier 2017-NM-127-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM 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 NPRM.

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a final 
rule titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, that rule 
included Amendment 21-78, which established Special Federal Aviation 
Regulation No. 88 (``SFAR 88'') at 14 CFR part 21. Subsequently, SFAR 
88 was amended by Amendment 21-82 (67 FR 57490, September 20, 2002; 
corrected at 67 FR 70809, November 26, 2002) and Amendment 21-83 (67 FR 
72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to 
change ``21-72'' to ``21-83'').
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the final rule published on 
May 7, 2001, we intended to adopt airworthiness directives to mandate 
any changes found necessary to address unsafe conditions identified as 
a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended

[[Page 5577]]

to define the unsafe conditions associated with fuel tank systems that 
require corrective actions. The percentage of operating time during 
which fuel tanks are exposed to flammable conditions is one of these 
criteria. The other three criteria address the failure types under 
evaluation: Single failures, single failures in combination with 
another latent condition(s), and in-service failure experience. For all 
four criteria, the evaluations included consideration of previous 
actions taken that may mitigate the need for further action.
    We have determined that the actions identified in this proposed AD 
are necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing 727-100/200 Airworthiness Limitations (AWLs) D6-
8766-AWL, dated December 2016. The service information describes AWL 
tasks that include airworthiness limitation instructions (ALIs) and 
critical design configuration control limitations (CDCCLs) related to 
fuel tank ignition prevention. 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 revision of the maintenance or 
inspection program to incorporate the ALI and CDCCL tasks described 
previously.
    This proposed AD would require revisions to certain operator 
maintenance documents to include new actions (e.g., inspections) and 
CDCCLs. Compliance with these actions and CDCCLs is required by 14 CFR 
91.403(c). For airplanes that have been previously modified, altered, 
or repaired in the areas addressed by this proposed AD, the operator 
may not be able to accomplish the actions described in the revisions. 
In this situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according to 
paragraph (k) of this proposed AD. The request should include a 
description of changes to the required inspections that will ensure the 
continued operational safety of the airplane.
    Notwithstanding any other maintenance or operational requirements, 
components that have been identified as airworthy or installed on the 
affected airplanes before accomplishing the revision of the airplane 
maintenance or inspection program specified in this proposed AD do not 
need to be reworked in accordance with the latest revision of the 
CDCCLs specified by this proposed AD for incorporation. However, once 
the airplane maintenance or inspection program has been revised as 
specified by this proposed AD, future maintenance actions on these 
components must be done in accordance with the CDCCLs specified by this 
proposed AD.

Related Rulemaking

    Five ADs are related to this NPRM. We have determined that certain 
requirements of those ADs may be terminated when the referenced AWLs 
specified in this proposed AD have been incorporated, as follows:
     The revision required by paragraph (g) of AD 2008-04-10 
R1, Amendment 39-16121 (74 FR 66227, December 15, 2009).
     The revision required by paragraph (h) of AD 2009-05-03, 
Amendment 39-15827 (74 FR 8851, February 27, 2009).
     The revision required by paragraph (j) of AD 2011-12-05, 
Amendment 39-16712 (76 FR 33991, June 10, 2011).
     The revision required by paragraph (h) of AD 2013-22-03, 
Amendment 39-17635 (78 FR 65193, October 31, 2013).
     The revision required by paragraphs (n)(1) and (n)(2) of 
AD 2013-24-15, Amendment 39-17692 (78 FR 72791, December 4, 2013).

Differences Between This Proposed AD and the Service Information

    AWL No. 28-AWL-03 identifies certain wire types. Paragraph (h)(1) 
of this proposed AD specifies additional acceptable wire types and 
cables.
    AWL No. 28-AWL-03 identifies certain sleeving materials. Paragraph 
(h)(2) of this proposed AD specifies additional acceptable sleeving 
materials.

Costs of Compliance

    We estimate that this proposed AD affects 20 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
----------------------------------------------------------------------------------------------------------------
Maintenance or inspection program    1 work-hour x $85 per hour               $0             $85          $1,700
 revision.                            = $85.
----------------------------------------------------------------------------------------------------------------

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 proposed 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 and associated appliances to the 
Director of the System Oversight Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications

[[Page 5578]]

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-2018-0031; Product Identifier 
2017-NM-127-AD.

(a) Comments Due Date

    We must receive comments by March 26, 2018.

(b) Affected ADs

    This AD affects the ADs specified in paragraphs (b)(1) through 
(b)(5) of this AD.
    (1) AD 2008-04-10 R1, Amendment 39-16121 (74 FR 66227, December 
15, 2009) (``AD 2008-04-10 R1'').
    (2) AD 2009-05-03, Amendment 39-15827 (74 FR 8851, February 27, 
2009) (``AD 2009-05-03'').
    (3) AD 2011-12-05, Amendment 39-16712 (76 FR 33991, June 10, 
2011) (``AD 2011-12-05'').
    (4) AD 2013-22-03, Amendment 39-17635 (78 FR 65193, October 31, 
2013) (``AD 2013-22-03'').
    (5) AD 2013-24-15, Amendment 39-17692 (78 FR 72791, December 4, 
2013) (``AD 2013-24-15'').

(c) Applicability

    This AD applies to The Boeing Company Model 727, 727C, 727-100, 
727-100C, 727-200, and 727-200F series airplanes, certificated in 
any category, with an original standard airworthiness certificate or 
original export certificate of airworthiness issued on or before the 
effective date of this AD.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

(e) Unsafe Condition

    This AD was prompted by significant changes made to the 
airworthiness limitations (AWLs) related to fuel tank ignition 
prevention. We are issuing this AD to prevent the potential for 
ignition sources inside fuel tanks caused by latent failures, 
alterations, repairs, or maintenance actions, which, in combination 
with flammable fuel vapors, could result in fuel tank explosions and 
consequent loss of the airplane.

(f) Compliance

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

(g) Maintenance or Inspection Program Revision

    Within 60 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate all 
information in Section A, including Subsections A.1 and A.2, of 
Boeing 727-100/200 Airworthiness Limitations (AWLs) D6-8766-AWL, 
dated December 2016. The initial compliance times for the 
airworthiness limitation instruction (ALI) items are within the 
applicable compliance times specified in paragraphs (g)(1) through 
(g)(6) of this AD.
    (1) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel 
Tank (Tank No. 2)'': at the applicable time specified in paragraph 
(g)(1)(i) or (g)(1)(ii) of this AD.
    (i) For airplanes that have been previously inspected as 
specified in 28-AWL-01 as of the effective date of this AD: Conduct 
the inspection within 120 months after the most recent inspection.
    (ii) For airplanes that have not been inspected as specified in 
28-AWL-01 as of the effective date of this AD: Conduct the 
inspection within 12 months after the effective date of this AD.
    (2) For AWL No. 28-AWL-16, ``Over-Current and Arcing Protection 
Electrical Design Features Operation--Boost Pump Ground Fault 
Interrupter (GFI)'': at the applicable time specified in paragraph 
(g)(2)(i) or (g)(2)(ii) of this AD.
    (i) For airplanes that have been previously inspected as 
specified in 28-AWL-16 as of the effective date of this AD: Conduct 
the inspection within 12 months after the most recent inspection.
    (ii) For airplanes that have not been inspected as specified in 
28-AWL-16 as of the effective date of this AD: Conduct the 
inspection within 90 days after the effective date of this AD.
    (3) For AWL No. 28-AWL-17, ``Auxiliary Tank Fuel Boost Pump 
Power Failed On Protection System'': at the applicable time 
specified in paragraph (g)(3)(i) or (g)(3)(ii) of this AD.
    (i) For airplanes that have been previously inspected as 
specified in 28-AWL-17 as of the effective date of this AD: Conduct 
the inspection within 12 months after the most recent inspection.
    (ii) For airplanes that have not been inspected as specified in 
28-AWL-17 as of the effective date of this AD: Conduct the 
inspection within 90 days after the effective date of this AD.
    (4) For AWL No. 28-AWL-18, ``Fuel Quantity Indicating System 
(FQIS)--Out-Tank Wiring Lightning Shield to Ground Termination and 
Joint Resistance for the Volumetric Top-Off (VTO) Unit (If 
Installed)'': at the applicable time specified in paragraph 
(g)(4)(i) or (g)(4)(ii) of this AD.
    (i) For airplanes that have been previously inspected as 
specified in 28-AWL-18 as of the effective date of this AD: Conduct 
the inspection within 120 months after the most recent inspection.
    (ii) For airplanes that have not been inspected as specified in 
28-AWL-18: Conduct the inspection within 12 months after the 
effective date of this AD.
    (5) For AWL No. 28-AWL-22, ``AC Fuel Boost Pump Bonding 
Installation'': at the applicable time specified in paragraph 
(g)(5)(i) or (g)(5)(ii) of this AD.
    (i) For airplanes that have been previously inspected as 
specified in 28-AWL-22 as of the effective date of this AD: Conduct 
the inspection within 72 months after the most recent inspection.
    (ii) For airplanes that have not been inspected as specified in 
28-AWL-22 as of the effective date of this AD: Conduct the 
inspection within 12 months after the effective date of this AD.
    (6) For AWL No. 28-AWL-24, ``Motor Operated Valve Bonding Jumper 
Installation--Fault Current Protection'': at the applicable time 
specified in paragraph (g)(6)(i) or (g)(6)(ii) of this AD.
    (i) For airplanes that have been previously inspected as 
specified in 28-AWL-24 as of the effective date of this AD: Conduct 
the inspection within 60 months after the most recent inspection.
    (ii) For airplanes that have not been inspected as specified in 
28-AWL-24 as of the effective date of this AD: Conduct the 
inspection within 12 months after the effective date of this AD.

(h) Additional Acceptable Wire Types and Sleeving

    (1) Where AWL No. 28-AWL-03 identifies wire types BMS 13-48, BMS 
13-58, and BMS 13-60, the following acceptable wire types and cables 
can be added to AWL No. 28-AWL-03: MIL-W-22759/16, SAE AS22759/16 
(Formerly M22759/16), MIL-W-22759/32, SAE AS22759/32 (Formerly 
M22759/32), MIL-W-22759/34, SAE AS22759/34 (Formerly M22759/34), 
MIL-W-22759/41, SAE AS22759/41 (Formerly M22759/41), MIL-W-22759/86, 
SAE AS22759/86 (Formerly M22759/86), MIL-W-22759/87, SAE AS22759/87 
(Formerly M22759/87), MIL-W-22759/92 and SAE AS22759/92 (Formerly 
M22759/92); and MIL-C-27500 cables that are constructed from the MIL

[[Page 5579]]

specification wire types identified above; and NEMA WC 27500 cables 
that are constructed from the SAE specification wire types 
identified above.
    (2) Where AWL No. 28-AWL-03 identifies TFE-2X Standard wall for 
wire sleeving, the following acceptable sleeving materials can be 
added to AWL No. 28-AWL-03: Roundit 2000NX and Varglas Type HO, HP, 
or HM, Grade A.

(i) No Alternative Actions, Intervals, and Critical Design 
Configuration Control Limitations (CDCCLs)

    After the maintenance or inspection program, as applicable, has 
been revised as required by paragraph (g) of this AD, no alternative 
actions (e.g., inspections), intervals, and CDCCLs may be used 
unless the actions, intervals, and CDCCLs are approved as an 
alternative method of compliance (AMOC), in accordance with the 
procedures specified in paragraph (k) of this AD.

(j) Terminating Actions

    Accomplishment of the revision required by paragraph (g) of this 
AD terminates the actions specified in paragraphs (j)(1) through 
(j)(5) of this AD for the airplane on which the revision has been 
incorporated.
    (1) The revision required by paragraph (g) of AD 2008-04-10 R1.
    (2) The revision required by paragraph (h) of AD 2009-05-03.
    (3) The revision required by paragraph (j) of AD 2011-12-05.
    (4) The revision required by paragraph (h) of AD 2013-22-03.
    (5) The revision required by paragraphs (n)(1) and (n)(2) of AD 
2013-24-15.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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 (l)(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 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.

(l) Related Information

    (1) For more information about this AD, contact Christopher 
Baker, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO 
Branch, 1601 Lind Avenue SW, Renton, WA 98057-3356; phone: 425-917-
6498; fax: 425-917-6590; email: [email protected].
    (2) 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; 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.

    Issued in Renton, Washington, on January 26, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-02085 Filed 2-7-18; 8:45 am]
 BILLING CODE 4910-13-P


