[Federal Register Volume 79, Number 101 (Tuesday, May 27, 2014)]
[Rules and Regulations]
[Pages 30005-30008]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-12093]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0618; Directorate Identifier 2007-NM-355-AD; 
Amendment 39-17844; AD 2014-09-09]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series 
airplanes. This AD was prompted by reports of two in-service 
occurrences on Model 737-400 airplanes of total loss of boost pump 
pressure of the fuel feed system, followed by loss of fuel system 
suction feed capability on one engine, and in-flight shutdown of the 
engine. This AD requires revising the maintenance program to 
incorporate a revision to the Airworthiness Limitations Section of the 
maintenance planning data (MPD) document. We are issuing this AD to 
detect and correct failure of the engine fuel suction feed of the fuel 
system, which, in the event of total loss of the fuel boost pumps, 
could result in dual engine flameout, inability to restart the engines, 
and consequent forced landing of the airplane.

DATES: This AD is effective July 1, 2014.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this 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 by searching for and locating Docket No. FAA-2008-
0618; 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: Sue Lucier, Aerospace Engineer, 
Propulsion Branch, ANM-140S, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6438; fax: 425-917-6590; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a second supplemental notice of proposed rulemaking 
(SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all 
The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series 
airplanes. The second SNPRM published in the Federal Register on July 
30, 2013 (78 FR 45898). The second SNPRM proposed to add Model 777F 
series airplanes to the applicability.
    We preceded the second SNPRM with the first SNPRM, which published 
in the Federal Register on March 7, 2013 (78 FR 14722). The first SNPRM 
proposed to revise the maintenance program to incorporate a revision to 
the Airworthiness Limitations Section of the maintenance planning data 
(MPD) document.
    We preceded the first SNPRM with a notice of proposed rulemaking 
(NPRM) that published in the Federal Register on June 6, 2008 (73 FR 
32253). The NPRM was prompted by reports of two in-service occurrences 
on Model 737-400 airplanes of total loss of boost pump pressure of the 
fuel feed system, followed by loss of fuel system suction feed 
capability on one engine, and in-flight shutdown of the engine. The 
subject area on Model 777 airplanes is almost identical to that area on 
Model 737-400 airplanes; therefore, Model 777 airplanes may be subject 
to the unsafe condition revealed on Model 737-400 airplanes. The NPRM 
proposed to require performing repetitive operational tests of the 
engine fuel suction feed of the fuel system, and other related testing 
if necessary.
    We are issuing this AD to detect and correct failure of the engine 
fuel suction feed of the fuel system, which, in the event of total loss 
of the fuel boost pumps, could result in dual engine flameout, 
inability to restart the engines, and consequent forced landing of the 
airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the second 
SNPRM (78 FR 45898, July 30, 2013) and the FAA's response to each 
comment. FedEx concurs with the proposed requirements.

Request To Allow the Use of Later Revisions of the Maintenance Planning 
Document (MPD)

    United Airlines (UAL) asked that we allow using the latest MPD 
revision of

[[Page 30006]]

May 2013 for accomplishing the required actions. UAL stated that 
paragraph (l) of the second SNPRM (78 FR 45898, July 30, 2013) provides 
credit for doing the actions required by paragraph (g) of the second 
SNPRM before the effective date of the AD, if the actions were done 
using Revision February 2012 of the MPD. UAL suggested that credit for 
Revision May 2013 of the MPD also be included in paragraph (l) of the 
second SNPRM.
    We agree to give credit for the latest revision of Section 9, 
Airworthiness Limitations (AWLs) and Certification Maintenance 
Requirements (CMRs), D622W001-9, which is Revision dated June 2013; 
provided the revised ``interval'' specified in Appendix 1 of this AD is 
incorporated into the existing maintenance program within 90 days after 
the effective date of this AD. We have revised paragraph (i) of this AD 
accordingly.

Request To Clarify Reason for the Unsafe Condition

    Boeing asked that we clarify the reason for the unsafe condition 
identified in the second SNPRM (78 FR 45898, July 30, 2013). Boeing 
asked that we provide additional clarification that there are no 
reports of any in-service events on Model 777 airplanes.
    We acknowledge the commenter's concern, but do not find it 
necessary to clarify the unsafe condition further. We clarified the 
reason for the unsafe condition in the first SNPRM (78 FR 45898, July 
30, 2013) per a similar request from Boeing regarding the fact that 
there had been no events on Model 777 airplanes. In light of this, we 
find that further clarification is not necessary. We have made no 
change to the final rule in this regard.

Change to Final Rule

    We removed the on-condition costs specified in the ``Costs of 
Compliance'' section of this final rule because there are no on-
condition actions.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed.

Costs of Compliance

    We estimate that this AD affects 676 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
             Action                    Labor cost            Cost per product           Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Maintenance Program Revision....  1 work-hour x $85    $85 per test................  $57,460, per test.
                                   per hour = $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.

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):

2014-09-09 The Boeing Company: Amendment 39-17844; Docket No. FAA-
2008-0618; Directorate Identifier 2007-NM-355-AD.

(a) Effective Date

    This AD is effective July 1, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 777-200, -200LR, 
-300, -300ER, and 777F series airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 2800, Aircraft 
Fuel System.

(e) Unsafe Condition

    This AD was prompted by reports of two in-service occurrences on 
Model 737-400 airplanes of total loss of boost pump pressure of the 
fuel feed system, followed by loss of fuel system suction feed 
capability on one engine, and in-flight shutdown of the engine. We 
are issuing this AD to detect and correct failure of the engine fuel 
suction feed of the fuel system, which, in the event of total loss 
of the fuel boost pumps, could result in dual engine flameout, 
inability to restart the engines, and consequent forced landing of 
the airplane.

(f) Compliance

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

(g) Maintenance Program Revision

    Within 90 days after the effective date of this AD: Revise the 
maintenance program to incorporate the airworthiness limitation

[[Page 30007]]

(AWL) identified in Appendix 1 of this AD, AWL No. 28-AWL-101, 
Engine Fuel Suction Feed Operational Test. The initial compliance 
time for accomplishing AWL No. 28-AWL-101 is within 7,500 flight 
hours or 3 years after the effective date of this AD, whichever is 
first.

(h) No Alternative Actions, Intervals, and/or Critical Design 
Configuration Control Limitations (CDCCLs)

    After accomplishing the revision required by paragraph (g) of 
this AD, no alternative actions (e.g., tests), intervals, or CDCCLs 
may be used unless the actions, intervals, or CDCCLs are approved as 
an alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (j) of this AD.

(i) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using AWL No. 28-AWL-101, Engine Fuel 
Suction Feed Operational Test, of Section D.2., Engine Suction Fuel 
System, of Section 9, Airworthiness Limitations (AWLs) and 
Certification Maintenance Requirements (CMRs), D622W001-9, Revision 
February 2012, or Revision June 2013, of the Boeing 777 Maintenance 
Planning Data (MPD) Document, provided the revised ``interval'' 
specified in Appendix 1 of this AD is incorporated into the existing 
maintenance program within 90 days after the effective date of this 
AD.

(j) 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 the Related Information 
section 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.

(k) Related Information

    (1) For more information about this AD, contact Sue Lucier, 
Aerospace Engineer, Propulsion Branch, ANM-140S, 1601 Lind Avenue 
SW., Renton, Washington 98057-3356; phone: 425-917-6438; fax: 425-
917-6590; email: [email protected].
    (2) For service information identified in this AD that is not 
incorporated by reference, contact Boeing Commercial Airplanes, 
Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, 
Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 
206-766-5680; Internet https://www.myboeingfleet.com.

(l) Material Incorporated by Reference

    None.

Appendix 1 of AD 2014-09-09

--------------------------------------------------------------------------------------------------------------------------------------------------------
             AWL No.                        Task                   Interval              Applicability                       Description
--------------------------------------------------------------------------------------------------------------------------------------------------------
28-AWL-101.......................  ALI..................  7,500 FH or 3 years,       ALL..................  Engine Fuel Suction Feed Operational Test.
                                                           whichever is first.
                                                                                                            An Engine Fuel Suction Feed Operational Test
                                                                                                             must be accomplished successfully on each
                                                                                                             engine individually. This test is required
                                                                                                             in order to protect against engine flameout
                                                                                                             during suction feed operations, and must
                                                                                                             meet the following requirements (refer to
                                                                                                             Boeing AMM 28-22-00):
                                                                                                            Fuel Tank Quantity Limitations:
                                                                                                               Engine No. 1
                                                                                                            a. The Center Tank Fuel Quantity must not
                                                                                                             exceed 5,000 lbs (2,270 kg).
                                                                                                            b. The Main Tank No. 1 Fuel Quantity must be
                                                                                                             between 1,400 lbs-1,600 lbs (600 kg-800
                                                                                                             kg).
                                                                                                            NOTE: Excess fuel can be transferred to Main
                                                                                                             Tank No. 2.
                                                                                                               Engine No. 2
                                                                                                            a. The Center Tank Fuel Quantity must not
                                                                                                             exceed 5,000 lbs (2,270 kg).
                                                                                                            b. The Main Tank No. 2 Fuel Quantity must be
                                                                                                             between 1,400 lbs-1,600 lbs (600 kg-800
                                                                                                             kg).
                                                                                                            NOTE: Excess fuel can be transferred to Main
                                                                                                             Tank No. 1.
                                                                                                            Test Procedural Limitations:
                                                                                                            1. The Fuel Cross-Feed Valve must be CLOSED.
                                                                                                            2. The APU Selector Switch must be OFF.
                                                                                                            3. Idle Engine Warm-up time of minimum two
                                                                                                             minutes with Boost Pump ON.
                                                                                                            4. Idle Engine Suction Feed (Boost Pump OFF)
                                                                                                             operation for a minimum of five minutes.
                                                                                                            NOTE: APU may be used to start the engines
                                                                                                             provided the Fuel Tank Quantity and Test
                                                                                                             Procedural Limitations are met.
                                                                                                            The test is considered a success if engine
                                                                                                             operation is maintained during the five-
                                                                                                             minute period and engine parameters (N1,
                                                                                                             N2, and Fuel Flow) do not decay relative to
                                                                                                             those observed with Boost Pump ON.
                                                                                                            A suction feed system that fails the
                                                                                                             operational test must be repaired or
                                                                                                             maintained, and successfully pass the
                                                                                                             Engine Suction Feed Operational Test prior
                                                                                                             to further flight.
--------------------------------------------------------------------------------------------------------------------------------------------------------



[[Page 30008]]

    Issued in Renton, Washington, on April 18, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-12093 Filed 5-23-14; 8:45 am]
BILLING CODE 4910-13-P