Document ID: FAA-2010-1272-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Boeing Co. Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F Series Airplanes
Posted Date: 2011-01-03T05:00Z

[Federal Register Volume 76, Number 1 (Monday, January 3, 2011)]
[Proposed Rules]
[Pages 31-34]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-33002]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1272; Directorate Identifier 2010-NM-226-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Model 727, 727C, 
727-100, 727-100C, 727-200, and 727-200F Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD would require replacing the 
existing unshielded fuel quantity indication system (FQIS) wire bundles 
with double shielded FQIS wire bundles, installing a new wire feed-
through fitting, and grounding the wire shields, as applicable; and 
doing repetitive low frequency eddy current (LFEC) inspections for 
cracking of the fuselage skin, and corrective actions if necessary. 
This proposed AD also would require revising the maintenance program to 
incorporate certain airworthiness limitations. This proposed AD was 
prompted by fuel system reviews conducted by the manufacturer. We are 
proposing this AD to increase the level of protection from lightning 
strikes and prevent 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.

DATES: We must receive comments on this proposed AD by February 17, 
2011.

ADDRESSES: You may send comments 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

[[Page 32]]

p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. 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; 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: Louis Natsiopoulos, Aerospace 
Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6478; fax (425) 917-6590; e-mail: 
elias.natsiopoulos@faa.gov.

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-2010-1272; 
Directorate Identifier 2010-NM-226-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

    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 
regulation 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, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 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 rule, 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 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 a 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 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.
    A safety assessment has determined that shielding was not provided 
for the FQIS wire bundles. Unshielded wire bundles could result in a 
reduced level of protection against a lightning strike which could be a 
potential ignition source for the fumes in the fuel tanks. This 
condition, if not corrected, could result in fuel tank explosions and 
consequent loss of the airplane.

Relevant Service Information

    We reviewed Boeing Service Bulletin 727-28-0131, dated August 18, 
2010. The service information describes procedures for the following:
     For airplanes in Groups 1, 12, 13, and 14: Replacing the 
FQIS wire bundles between the fitting and ground brackets at the 
pressure seal and the tank connectors on the wing tanks with double 
shielded wire bundles; installing a new wire feed-through fitting and 
ground brackets for the wires at the pressure seal, and ground brackets 
at the wing tank connectors; and grounding the wire shields at the 
pressure seal feed-through fitting and ground brackets and at the tank 
connector brackets.
     For airplanes in Groups 2 through 11 and 15 through 49: 
Replacing the FQIS wire bundles between the pressure seal and the 
volumetric top-off (VTO) connectors with double shielded wire bundles 
and working the ground wires at the VTO connectors.
     For all airplanes: Doing repetitive LFEC inspections for 
cracking in the fuselage skin on the left and right sides of the 
airplane, and contacting Boeing for repair instructions and doing the 
repair if necessary.
    We have also reviewed Section 9 of the Boeing 727-100/200 
Airworthiness Limitations (AWLs), D6-8766-AWL, Revision August 2010. 
Sub-Section D of Section 9 of the Boeing 727-100/200 Airworthiness 
Limitations (AWLs), D6-8766-AWL describes AWLs for fuel tank systems, 
including the following fuel system AWLs:
     AWL No. 28-AWL-18 which is a check of the fuel quantity 
indicating system (FQIS)--out-tank wiring lightning shield to ground 
termination, applicable to all Model 727-100 and -200 airplanes that 
have incorporated Boeing Service Bulletin 727-28-0131.
     AWL No. 28-AWL-19 which is a critical design configuration 
control limitation (CDCCL) that specifies to do a check of the FQIS--
out-tank wiring lightning shield to ground termination, following any 
FQIS out-tank wire bundle replacement, wire bundle shield repair or 
shield path to ground reconnection, applicable to all Model 727-100 and 
-200 airplanes that have incorporated Boeing Service Bulletin 727-28-
0131.

[[Page 33]]

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 Proposed Rule and Service Bulletin.''

Differences Between Proposed Rule and Service Bulletin

    Although Boeing Service Bulletin 727-28-0131, dated August 18, 
2010, specifies that operators may contact the manufacturer for 
disposition of certain repair conditions, this proposed AD would 
require operators to repair those cracks using a method approved by the 
FAA.

Costs of Compliance

    We estimate that this proposed AD will affect 566 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
----------------------------------------------------------------------------------------------------------------
Installation...................  Between 86 and 247      Between $16,191    Between $23,501    Up to
                                  work-hours x $85 per    and $34,712.\1\    and $55,707.\1\    $27,195,925.\2\
                                  hour = Between $7,310-
                                  $20,995.\1\
Inspection.....................  2 work-hours x $85 per  0................  170..............  96,220 per
                                  hour = $170 per                                               inspection
                                  inspection cycle.                                             cycle.
Maintenance Program Revision...  1 work-hour x $85 per   0................  85...............  48,110.
                                  hour = $85.
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\1\ Depending on configuration.
\2\ The cost on U.S. operators is based on configuration and number of airplanes in that configuration.

We have received no definitive data that would enable us to provide a 
cost estimate for the on-condition action specified in this proposed 
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

    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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

The Boeing Company: Docket No. FAA-2010-1272; Directorate Identifier 
2010-NM-226-AD.

Comments Due Date

    (a) We must receive comments by February 17, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to The Boeing Company Model 727, 727C, 727-
100, 727-100C, 727-200, and 727-200F series airplanes, all variable 
numbers, certificated in any category.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections 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 (l) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued operational safety of the airplane.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 28, Fuel.

Unsafe Condition

    (e) This AD was prompted by fuel system reviews conducted by the 
manufacturer. We are issuing this AD to increase the level of 
protection from lightning strikes and prevent 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.

Compliance

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

[[Page 34]]

Installation

    (g) Within 60 months after the effective date of this AD, 
install double shielded fuel quantity indicating system (FQIS) wire 
bundles, install a new wire feed-through fitting, and ground the 
wire shields, as applicable, in accordance with Part 1 of the 
Accomplishment Instructions of Boeing Service Bulletin 727-28-0131, 
dated August 18, 2010.

Repetitive Inspections

    (h) At the applicable times specified in paragraphs (h)(1) or 
(h)(2) of this AD, do low frequency eddy current (LFEC) inspections 
for cracking of the fuselage skin, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Service Bulletin 727-28-0131, 
dated August 18, 2010.
    (1) For Model 727, 727-100, 727-100C, and 727C series airplanes: 
Before the accumulation of 45,000 total flight cycles, or within 
8,000 flight cycles after the effective date of this AD, whichever 
occurs later. Repeat the inspections thereafter at intervals not to 
exceed 8,000 flight cycles.
    (2) For Model 727-200 and 727-200F series airplanes: Before the 
accumulation of 45,000 total flight cycles, or within 16,000 flight 
cycles after the effective date of this AD, whichever occurs later. 
Repeat the inspections thereafter at intervals not to exceed 16,000 
flight cycles.
    (i) If any cracking is found during any inspection required by 
paragraph (h) of this AD: Before further flight, repair the crack in 
accordance with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA. For a repair method to be approved, 
the repair must meet the certification basis of the airplane, and 
the approval must specifically refer to this AD.

Maintenance Program Revision

    (j) Before or concurrently with doing the actions required by 
paragraph (g) of this AD, or within 30 days after the effective date 
of this AD, whichever occurs later: Revise the maintenance program 
by incorporating airworthiness limitations (AWL) No. 28-AWL-18 and 
28-AWL-19 in Section D of Section 9 (``AIRWORTHINESS LIMITATIONS--
FUEL SYSTEMS'') of the Boeing 727-100/200 Airworthiness Limitations 
(AWLs) Document, D6-8766-AWL, Revision August 2010. The initial 
compliance time for AWL No. 28-AWL-18 is within 10 years after the 
accomplishment of paragraph (g) of this AD, or within 10 years after 
the effective date of this AD, whichever occurs later.

No Alternative Inspections, Inspection Intervals, or Critical Design 
Configuration Control Limitations (CDCCLs)

    (k) After accomplishing the action specified in paragraph (j) of 
this AD, no alternative inspections, inspection intervals, or CDCCLs 
may be used unless the inspections, intervals, or CDCCLs are 
approved as an Alternative Method of Compliance (AMOC) in accordance 
with the procedures specified in paragraph (l) of this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(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 the Related Information 
section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your Principal 
Maintenance Inspector or Principal Avionics Inspector, as 
appropriate, or lacking a principal inspector, your local Flight 
Standards District Office.

Related Information

    (m) For more information about this AD, contact Louis 
Natsiopoulos, Aerospace Engineer, Systems and Equipment Branch, ANM-
130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, 
SW., Renton, Washington 98057-3356; telephone (425) 917-6478; fax 
(425) 917-6590; e-mail: elias.natsiopoulos@faa.gov.
    (n) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You 
may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.

    Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-33002 Filed 12-30-10; 8:45 am]
BILLING CODE 4910-13-P